GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 100,000 Max Cl/Cd: 57.92 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe335-il-100000-n5.txt Download as CSV file: xf-goe335-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3048 0.09818 0.09352 -0.0265 1.0000 0.0365
-7.500 -0.3096 0.09678 0.09223 -0.0265 1.0000 0.0369
-7.250 -0.3132 0.09530 0.09085 -0.0275 1.0000 0.0372
-7.000 -0.3120 0.09314 0.08877 -0.0290 1.0000 0.0374
-6.750 -0.3096 0.09079 0.08648 -0.0306 1.0000 0.0376
-6.500 -0.3066 0.08829 0.08405 -0.0316 1.0000 0.0376
-6.250 -0.3041 0.08582 0.08163 -0.0323 1.0000 0.0377
-6.000 -0.2945 0.08273 0.07856 -0.0346 0.9983 0.0378
-5.750 -0.2616 0.07764 0.07338 -0.0423 0.9909 0.0379
-5.500 -0.2294 0.07259 0.06824 -0.0490 0.9835 0.0379
-5.250 -0.1959 0.06752 0.06305 -0.0554 0.9767 0.0380
-5.000 -0.1952 0.06305 0.05876 -0.0516 0.9698 0.0423
-4.750 -0.1400 0.05934 0.05472 -0.0645 0.9602 0.0513
-4.500 -0.1141 0.05255 0.04786 -0.0675 0.9539 0.0361
-4.250 -0.0821 0.04801 0.04315 -0.0720 0.9438 0.0347
-4.000 -0.0390 0.04295 0.03776 -0.0783 0.9350 0.0359
-3.750 0.0075 0.03784 0.03212 -0.0838 0.9264 0.0377
-3.500 0.0420 0.03322 0.02706 -0.0866 0.9150 0.0383
-3.250 0.0703 0.03141 0.02522 -0.0884 0.9032 0.0431
-3.000 0.1070 0.02815 0.02147 -0.0906 0.8932 0.0456
-2.750 0.1446 0.02515 0.01784 -0.0924 0.8831 0.0483
-2.500 0.1799 0.02315 0.01513 -0.0933 0.8712 0.0516
-2.250 0.2128 0.02105 0.01261 -0.0942 0.8600 0.0527
-2.000 0.2452 0.01966 0.01092 -0.0949 0.8495 0.0544
-1.750 0.2772 0.01894 0.01002 -0.0956 0.8391 0.0596
-1.500 0.3090 0.01800 0.00878 -0.0960 0.8285 0.0611
-1.250 0.3386 0.01719 0.00777 -0.0959 0.8167 0.0614
-1.000 0.3674 0.01654 0.00695 -0.0957 0.8048 0.0621
-0.750 0.3955 0.01601 0.00630 -0.0955 0.7926 0.0630
-0.500 0.4230 0.01559 0.00577 -0.0951 0.7799 0.0645
-0.250 0.4501 0.01523 0.00532 -0.0946 0.7667 0.0670
0.000 0.4767 0.01497 0.00500 -0.0940 0.7528 0.0723
0.250 0.5034 0.01476 0.00473 -0.0935 0.7383 0.0826
0.500 0.5300 0.01450 0.00452 -0.0930 0.7228 0.1224
0.750 0.5509 0.01310 0.00454 -0.0919 0.7068 0.6068
1.000 0.5901 0.01258 0.00434 -0.0936 0.6876 1.0000
1.250 0.6155 0.01269 0.00425 -0.0928 0.6684 1.0000
1.500 0.6404 0.01283 0.00422 -0.0919 0.6470 1.0000
1.750 0.6654 0.01298 0.00419 -0.0911 0.6248 1.0000
2.000 0.6901 0.01316 0.00421 -0.0902 0.6001 1.0000
2.250 0.7145 0.01338 0.00426 -0.0894 0.5743 1.0000
2.500 0.7388 0.01362 0.00434 -0.0885 0.5492 1.0000
2.750 0.7631 0.01390 0.00445 -0.0877 0.5265 1.0000
3.000 0.7874 0.01420 0.00463 -0.0870 0.5070 1.0000
3.250 0.8118 0.01452 0.00483 -0.0862 0.4903 1.0000
3.500 0.8363 0.01486 0.00507 -0.0856 0.4760 1.0000
3.750 0.8610 0.01522 0.00536 -0.0850 0.4640 1.0000
4.000 0.8858 0.01559 0.00567 -0.0844 0.4539 1.0000
4.250 0.9109 0.01595 0.00603 -0.0839 0.4446 1.0000
4.500 0.9358 0.01635 0.00640 -0.0834 0.4358 1.0000
4.750 0.9606 0.01674 0.00683 -0.0829 0.4266 1.0000
5.000 0.9853 0.01714 0.00726 -0.0823 0.4173 1.0000
5.250 1.0099 0.01757 0.00769 -0.0818 0.4087 1.0000
5.500 1.0345 0.01796 0.00822 -0.0813 0.3999 1.0000
5.750 1.0593 0.01840 0.00873 -0.0808 0.3927 1.0000
6.000 1.0835 0.01881 0.00927 -0.0802 0.3841 1.0000
6.250 1.1076 0.01924 0.00982 -0.0796 0.3758 1.0000
6.500 1.1291 0.01958 0.01027 -0.0785 0.3600 1.0000
6.750 1.1468 0.01981 0.01056 -0.0768 0.3315 1.0000
7.000 1.1670 0.02015 0.01101 -0.0755 0.3101 1.0000
7.250 1.1867 0.02052 0.01149 -0.0742 0.2828 1.0000
7.500 1.2045 0.02106 0.01201 -0.0726 0.2327 1.0000
7.750 1.2055 0.02349 0.01338 -0.0695 0.0937 1.0000
8.000 1.2086 0.02603 0.01541 -0.0666 0.0341 1.0000
8.250 1.2202 0.02749 0.01700 -0.0644 0.0274 1.0000
8.750 1.2386 0.03048 0.02035 -0.0596 0.0219 1.0000
9.000 1.2447 0.03195 0.02206 -0.0568 0.0205 1.0000
9.250 1.2467 0.03354 0.02387 -0.0537 0.0196 1.0000
9.500 1.2464 0.03532 0.02585 -0.0505 0.0190 1.0000
9.750 1.2446 0.03731 0.02802 -0.0477 0.0185 1.0000
10.000 1.2425 0.03946 0.03035 -0.0453 0.0181 1.0000
10.250 1.2397 0.04188 0.03292 -0.0434 0.0175 1.0000
10.500 1.2377 0.04444 0.03562 -0.0418 0.0169 1.0000
10.750 1.2359 0.04722 0.03851 -0.0404 0.0161 1.0000
11.000 1.2357 0.05008 0.04147 -0.0391 0.0153 1.0000
11.250 1.2405 0.05302 0.04450 -0.0375 0.0145 1.0000
11.500 1.2521 0.05614 0.04779 -0.0358 0.0141 1.0000
11.750 1.2585 0.05905 0.05097 -0.0348 0.0139 1.0000
12.000 1.2623 0.06221 0.05437 -0.0341 0.0138 1.0000
12.250 1.2630 0.06569 0.05810 -0.0336 0.0137 1.0000
12.500 1.2600 0.06955 0.06223 -0.0334 0.0136 1.0000
12.750 1.2541 0.07377 0.06671 -0.0337 0.0136 1.0000
13.000 1.2460 0.07834 0.07153 -0.0344 0.0136 1.0000
13.250 1.2360 0.08326 0.07671 -0.0357 0.0136 1.0000
13.500 1.2241 0.08862 0.08231 -0.0375 0.0136 1.0000
13.750 1.2110 0.09436 0.08828 -0.0399 0.0136 1.0000
14.000 1.1974 0.10044 0.09457 -0.0427 0.0136 1.0000
14.250 1.1831 0.10697 0.10131 -0.0462 0.0137 1.0000
14.500 1.1686 0.11395 0.10848 -0.0502 0.0137 1.0000
14.750 1.1539 0.12137 0.11608 -0.0547 0.0138 1.0000
15.000 1.1395 0.12911 0.12398 -0.0594 0.0139 1.0000
15.250 1.1254 0.13721 0.13222 -0.0645 0.0140 1.0000
15.750 0.9216 0.14168 0.13746 -0.0639 0.0149 1.0000
16.000 0.9040 0.15002 0.14594 -0.0692 0.0153 1.0000
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Polar data table (+)
Polar graphs
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