GOE 703 AIRFOIL (goe703-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 703 AIRFOIL (goe703-il) Reynolds number: 500,000 Max Cl/Cd: 67 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe703-il-500000.txt Download as CSV file: xf-goe703-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 703 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.8007 0.10547 0.10188 -0.0659 1.0000 0.0367
-18.750 -0.8785 0.08867 0.08468 -0.0763 1.0000 0.0363
-18.500 -0.9111 0.08041 0.07619 -0.0811 1.0000 0.0363
-18.250 -0.9364 0.07372 0.06931 -0.0844 1.0000 0.0364
-18.000 -0.9536 0.06855 0.06397 -0.0867 1.0000 0.0364
-17.750 -0.9677 0.06407 0.05934 -0.0882 1.0000 0.0364
-17.500 -0.9791 0.06015 0.05527 -0.0891 1.0000 0.0365
-17.250 -0.9875 0.05678 0.05177 -0.0895 1.0000 0.0366
-17.000 -0.9947 0.05375 0.04862 -0.0896 1.0000 0.0368
-16.750 -1.0004 0.05099 0.04573 -0.0892 1.0000 0.0370
-16.500 -1.0037 0.04857 0.04320 -0.0886 1.0000 0.0370
-16.250 -1.0079 0.04630 0.04081 -0.0876 1.0000 0.0373
-16.000 -1.0081 0.04435 0.03875 -0.0865 1.0000 0.0374
-15.750 -1.0105 0.04245 0.03673 -0.0850 1.0000 0.0377
-15.500 -1.0100 0.04079 0.03497 -0.0834 1.0000 0.0378
-15.250 -1.0110 0.03923 0.03329 -0.0815 1.0000 0.0381
-15.000 -1.0099 0.03784 0.03180 -0.0794 1.0000 0.0382
-14.750 -1.0081 0.03661 0.03047 -0.0772 1.0000 0.0383
-14.500 -0.9970 0.03516 0.02900 -0.0758 1.0000 0.0387
-14.250 -0.9876 0.03397 0.02780 -0.0741 1.0000 0.0390
-14.000 -0.9801 0.03295 0.02677 -0.0721 1.0000 0.0392
-13.750 -0.9734 0.03197 0.02577 -0.0698 1.0000 0.0395
-13.500 -0.9671 0.03107 0.02483 -0.0674 1.0000 0.0397
-13.250 -0.9620 0.03023 0.02398 -0.0647 1.0000 0.0400
-13.000 -0.9585 0.02948 0.02320 -0.0616 1.0000 0.0403
-12.750 -0.9573 0.02883 0.02253 -0.0581 0.9999 0.0406
-12.500 -0.9283 0.02779 0.02144 -0.0598 0.9979 0.0411
-12.250 -0.8985 0.02680 0.02039 -0.0615 0.9950 0.0416
-12.000 -0.8695 0.02584 0.01938 -0.0630 0.9911 0.0421
-11.750 -0.8419 0.02496 0.01844 -0.0641 0.9867 0.0426
-11.500 -0.8129 0.02403 0.01745 -0.0655 0.9824 0.0432
-11.250 -0.7879 0.02291 0.01635 -0.0662 0.9767 0.0439
-11.000 -0.7620 0.02205 0.01550 -0.0669 0.9691 0.0447
-10.750 -0.7369 0.02126 0.01470 -0.0673 0.9606 0.0454
-10.500 -0.7079 0.02050 0.01392 -0.0683 0.9534 0.0463
-10.250 -0.6766 0.01980 0.01316 -0.0698 0.9455 0.0471
-10.000 -0.6398 0.01909 0.01239 -0.0723 0.9378 0.0481
-9.750 -0.6028 0.01807 0.01140 -0.0754 0.9293 0.0497
-9.500 -0.5566 0.01734 0.01064 -0.0800 0.9212 0.0512
-9.250 -0.5096 0.01672 0.00995 -0.0847 0.9115 0.0532
-9.000 -0.4663 0.01597 0.00917 -0.0888 0.8992 0.0555
-8.750 -0.4309 0.01551 0.00865 -0.0910 0.8842 0.0585
-8.500 -0.4033 0.01502 0.00811 -0.0916 0.8690 0.0617
-8.250 -0.3781 0.01466 0.00768 -0.0915 0.8547 0.0661
-8.000 -0.3593 0.01427 0.00728 -0.0901 0.8408 0.0717
-7.750 -0.3421 0.01390 0.00691 -0.0883 0.8278 0.0804
-7.500 -0.3244 0.01351 0.00656 -0.0866 0.8150 0.0969
-7.250 -0.3093 0.01317 0.00631 -0.0843 0.8016 0.1170
-7.000 -0.2919 0.01291 0.00608 -0.0824 0.7888 0.1338
-6.750 -0.2740 0.01272 0.00588 -0.0805 0.7757 0.1472
-6.500 -0.2560 0.01255 0.00570 -0.0786 0.7626 0.1581
-6.250 -0.2386 0.01237 0.00551 -0.0767 0.7496 0.1699
-6.000 -0.2213 0.01220 0.00533 -0.0746 0.7360 0.1800
-5.750 -0.2025 0.01208 0.00517 -0.0728 0.7228 0.1896
-5.500 -0.1851 0.01193 0.00500 -0.0708 0.7109 0.2002
-5.250 -0.1667 0.01179 0.00485 -0.0689 0.6996 0.2108
-5.000 -0.1480 0.01169 0.00471 -0.0671 0.6893 0.2226
-4.750 -0.1303 0.01153 0.00458 -0.0651 0.6796 0.2345
-4.500 -0.1119 0.01142 0.00444 -0.0632 0.6707 0.2477
-4.000 -0.0749 0.01115 0.00421 -0.0595 0.6554 0.2786
-3.750 -0.0578 0.01099 0.00409 -0.0574 0.6483 0.2995
-3.500 -0.0422 0.01077 0.00397 -0.0550 0.6416 0.3253
-3.250 -0.0304 0.01048 0.00382 -0.0518 0.6353 0.3631
-3.000 -0.0245 0.01010 0.00366 -0.0475 0.6294 0.4217
-2.750 -0.0275 0.00960 0.00350 -0.0413 0.6242 0.4985
-2.500 -0.0329 0.00917 0.00335 -0.0343 0.6188 0.5719
-2.250 -0.0389 0.00885 0.00328 -0.0271 0.6138 0.6392
-2.000 -0.0344 0.00864 0.00333 -0.0219 0.6088 0.7084
-1.750 -0.0110 0.00858 0.00347 -0.0206 0.6037 0.7590
-1.500 0.0101 0.00864 0.00358 -0.0188 0.5982 0.7896
-1.250 0.0375 0.00878 0.00371 -0.0185 0.5932 0.8101
-1.000 0.0571 0.00893 0.00383 -0.0164 0.5883 0.8260
-0.750 0.0975 0.00912 0.00404 -0.0188 0.5833 0.8362
-0.250 0.1512 0.00949 0.00433 -0.0178 0.5734 0.8537
0.000 0.1501 0.00960 0.00439 -0.0114 0.5691 0.8647
0.250 0.2011 0.00987 0.00467 -0.0161 0.5643 0.8678
0.500 0.2454 0.01018 0.00496 -0.0193 0.5588 0.8710
0.750 0.2776 0.01047 0.00520 -0.0199 0.5540 0.8761
1.000 0.2927 0.01067 0.00534 -0.0170 0.5493 0.8839
1.250 0.3415 0.01105 0.00573 -0.0211 0.5444 0.8852
1.500 0.3877 0.01147 0.00613 -0.0246 0.5388 0.8862
1.750 0.4326 0.01192 0.00652 -0.0278 0.5332 0.8873
2.000 0.4732 0.01228 0.00684 -0.0303 0.5281 0.8889
2.250 0.5080 0.01252 0.00710 -0.0315 0.5217 0.8918
2.500 0.5107 0.01250 0.00706 -0.0262 0.5167 0.9012
2.750 0.5566 0.01292 0.00740 -0.0298 0.5097 0.9022
3.000 0.5988 0.01318 0.00769 -0.0325 0.5032 0.9036
3.250 0.6342 0.01335 0.00783 -0.0340 0.4969 0.9051
3.500 0.6653 0.01352 0.00794 -0.0347 0.4905 0.9070
3.750 0.6919 0.01358 0.00804 -0.0345 0.4843 0.9100
4.000 0.6892 0.01355 0.00800 -0.0283 0.4788 0.9187
4.250 0.7218 0.01370 0.00809 -0.0294 0.4719 0.9198
4.500 0.7546 0.01377 0.00820 -0.0305 0.4647 0.9210
4.750 0.7838 0.01389 0.00828 -0.0309 0.4565 0.9226
5.000 0.8116 0.01400 0.00838 -0.0310 0.4488 0.9247
5.250 0.8320 0.01410 0.00847 -0.0296 0.4408 0.9284
5.500 0.8284 0.01417 0.00850 -0.0232 0.4348 0.9358
5.750 0.8606 0.01423 0.00860 -0.0243 0.4265 0.9368
6.000 0.8887 0.01439 0.00871 -0.0246 0.4182 0.9383
6.250 0.9158 0.01448 0.00882 -0.0247 0.4106 0.9400
6.500 0.9351 0.01463 0.00894 -0.0232 0.4020 0.9431
6.750 0.9233 0.01472 0.00904 -0.0152 0.3969 0.9514
7.000 0.9516 0.01481 0.00912 -0.0156 0.3877 0.9526
7.250 0.9770 0.01497 0.00926 -0.0155 0.3787 0.9541
7.500 1.0018 0.01513 0.00942 -0.0153 0.3692 0.9562
7.750 1.0198 0.01535 0.00961 -0.0138 0.3609 0.9594
8.000 1.0139 0.01556 0.00985 -0.0073 0.3549 0.9662
8.500 1.0672 0.01597 0.01023 -0.0081 0.3363 0.9689
8.750 1.0886 0.01629 0.01051 -0.0075 0.3275 0.9710
9.000 1.1082 0.01654 0.01079 -0.0066 0.3182 0.9736
9.250 1.1130 0.01701 0.01123 -0.0029 0.3102 0.9783
9.500 1.1322 0.01732 0.01156 -0.0020 0.3007 0.9808
9.750 1.1553 0.01772 0.01194 -0.0022 0.2895 0.9824
10.250 1.1908 0.01879 0.01296 -0.0009 0.2650 0.9869
10.500 1.2031 0.01950 0.01365 0.0005 0.2520 0.9899
10.750 1.2137 0.02038 0.01449 0.0020 0.2380 0.9928
11.000 1.2299 0.02132 0.01537 0.0020 0.2217 0.9948
11.250 1.2423 0.02246 0.01645 0.0025 0.2064 0.9972
11.500 1.2532 0.02378 0.01771 0.0029 0.1923 0.9993
11.750 1.2525 0.02515 0.01905 0.0055 0.1829 1.0000
12.000 1.2494 0.02627 0.02018 0.0089 0.1766 1.0000
12.250 1.2421 0.02769 0.02158 0.0125 0.1707 1.0000
12.500 1.2399 0.02890 0.02282 0.0156 0.1667 1.0000
12.750 1.2378 0.03019 0.02413 0.0184 0.1625 1.0000
13.000 1.2332 0.03169 0.02565 0.0213 0.1589 1.0000
13.250 1.2287 0.03328 0.02725 0.0241 0.1556 1.0000
13.500 1.2305 0.03451 0.02853 0.0262 0.1530 1.0000
13.750 1.2300 0.03597 0.03003 0.0284 0.1499 1.0000
14.000 1.2275 0.03764 0.03172 0.0305 0.1468 1.0000
14.250 1.2233 0.03951 0.03359 0.0326 0.1439 1.0000
14.500 1.2249 0.04100 0.03513 0.0343 0.1413 1.0000
14.750 1.2269 0.04250 0.03668 0.0359 0.1385 1.0000
15.000 1.2269 0.04421 0.03843 0.0375 0.1355 1.0000
15.250 1.2239 0.04625 0.04048 0.0390 0.1328 1.0000
15.500 1.2226 0.04818 0.04244 0.0404 0.1302 1.0000
15.750 1.2270 0.04971 0.04403 0.0414 0.1274 1.0000
16.000 1.2278 0.05157 0.04593 0.0425 0.1244 1.0000
16.250 1.2247 0.05386 0.04823 0.0435 0.1212 1.0000
16.500 1.2245 0.05595 0.05037 0.0444 0.1178 1.0000
16.750 1.2262 0.05793 0.05239 0.0451 0.1136 1.0000
17.000 1.2211 0.06062 0.05509 0.0458 0.1096 1.0000
17.250 1.2225 0.06271 0.05723 0.0464 0.1044 1.0000
17.500 1.2186 0.06542 0.05996 0.0468 0.1001 1.0000
17.750 1.2172 0.06792 0.06249 0.0472 0.0936 1.0000
18.000 1.2118 0.07094 0.06551 0.0474 0.0874 1.0000
18.250 1.2058 0.07407 0.06864 0.0475 0.0818 1.0000
18.500 1.2001 0.07719 0.07177 0.0475 0.0766 1.0000
18.750 1.1910 0.08080 0.07538 0.0474 0.0732 1.0000
19.000 1.1855 0.08402 0.07863 0.0472 0.0708 1.0000
19.250 1.1783 0.08752 0.08215 0.0469 0.0687 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 703 AIRFOIL (goe703-il)