GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.62 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe244-il-1000000.txt Download as CSV file: xf-goe244-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 244 (MVA PR.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.2948 0.09192 0.08932 -0.1239 0.7805 0.0245
-10.500 0.2877 0.08669 0.08404 -0.1270 0.7760 0.0254
-10.250 0.2921 0.08315 0.08049 -0.1285 0.7712 0.0254
-10.000 0.3014 0.08029 0.07763 -0.1289 0.7660 0.0256
-9.750 0.3136 0.07828 0.07560 -0.1292 0.7600 0.0258
-9.500 0.3251 0.07622 0.07350 -0.1298 0.7539 0.0259
-9.250 0.3365 0.07408 0.07136 -0.1304 0.7480 0.0261
-9.000 0.3470 0.07187 0.06913 -0.1312 0.7414 0.0263
-8.750 0.3569 0.06959 0.06681 -0.1320 0.7352 0.0266
-8.500 0.3664 0.06711 0.06434 -0.1330 0.7294 0.0270
-8.250 0.3753 0.06456 0.06176 -0.1340 0.7227 0.0274
-8.000 0.3828 0.06179 0.05895 -0.1352 0.7165 0.0281
-7.750 0.3737 0.05481 0.05198 -0.1400 0.7123 0.0292
-7.500 0.3770 0.05108 0.04824 -0.1412 0.7062 0.0295
-7.250 0.3887 0.04939 0.04652 -0.1416 0.6993 0.0297
-7.000 0.4007 0.04753 0.04466 -0.1424 0.6938 0.0299
-6.750 0.4120 0.04563 0.04275 -0.1432 0.6867 0.0301
-6.500 0.4218 0.04358 0.04067 -0.1441 0.6798 0.0304
-6.250 0.4009 0.05453 0.05156 -0.1524 0.6926 0.0303
-6.000 0.4182 0.05223 0.04923 -0.1555 0.6856 0.0307
-5.750 0.5735 0.01553 0.01059 -0.2464 0.6796 0.0298
-5.500 0.6073 0.01502 0.00994 -0.2479 0.6736 0.0295
-5.250 0.6403 0.01415 0.00895 -0.2494 0.6666 0.0296
-5.000 0.6720 0.01367 0.00834 -0.2504 0.6599 0.0295
-4.750 0.7044 0.01308 0.00768 -0.2515 0.6534 0.0295
-4.500 0.7358 0.01250 0.00701 -0.2524 0.6459 0.0297
-4.250 0.7672 0.01201 0.00648 -0.2532 0.6390 0.0299
-4.000 0.7983 0.01166 0.00609 -0.2540 0.6309 0.0302
-3.750 0.8284 0.01144 0.00580 -0.2545 0.6224 0.0305
-3.500 0.8593 0.01121 0.00554 -0.2551 0.6138 0.0308
-3.250 0.8888 0.01109 0.00534 -0.2555 0.6044 0.0311
-3.000 0.9195 0.01092 0.00514 -0.2561 0.5954 0.0313
-2.750 0.9487 0.01085 0.00499 -0.2564 0.5847 0.0316
-2.500 0.9783 0.01076 0.00485 -0.2567 0.5725 0.0319
-2.250 1.0071 0.01074 0.00474 -0.2570 0.5587 0.0322
-2.000 1.0347 0.01078 0.00468 -0.2570 0.5411 0.0325
-1.750 1.0609 0.01091 0.00467 -0.2567 0.5179 0.0329
-1.500 1.0846 0.01119 0.00476 -0.2559 0.4902 0.0333
-1.250 1.1096 0.01137 0.00477 -0.2556 0.4641 0.0341
-1.000 1.1344 0.01157 0.00484 -0.2551 0.4448 0.0348
-0.750 1.1593 0.01176 0.00493 -0.2546 0.4304 0.0357
-0.500 1.1836 0.01199 0.00505 -0.2540 0.4181 0.0366
-0.250 1.2095 0.01212 0.00514 -0.2536 0.4098 0.0376
0.000 1.2335 0.01234 0.00527 -0.2530 0.4009 0.0390
0.250 1.2594 0.01245 0.00537 -0.2526 0.3951 0.0416
0.500 1.2849 0.01256 0.00552 -0.2523 0.3892 0.0678
0.750 1.3071 0.01275 0.00571 -0.2513 0.3828 0.0904
1.000 1.3338 0.01269 0.00588 -0.2514 0.3783 0.2083
1.250 1.3561 0.01284 0.00607 -0.2504 0.3743 0.2314
1.500 1.3788 0.01307 0.00630 -0.2495 0.3700 0.2495
1.750 1.4008 0.01336 0.00658 -0.2486 0.3652 0.2654
2.000 1.4232 0.01363 0.00686 -0.2477 0.3611 0.2814
2.250 1.4478 0.01381 0.00709 -0.2472 0.3586 0.3017
2.500 1.4715 0.01402 0.00735 -0.2466 0.3557 0.3281
2.750 1.4943 0.01428 0.00765 -0.2459 0.3525 0.3603
3.000 1.5158 0.01460 0.00803 -0.2450 0.3493 0.3994
3.250 1.5353 0.01502 0.00846 -0.2437 0.3455 0.4263
3.500 1.5561 0.01538 0.00884 -0.2426 0.3429 0.4433
3.750 1.5789 0.01565 0.00914 -0.2419 0.3411 0.4547
4.000 1.6007 0.01597 0.00946 -0.2410 0.3384 0.4643
4.250 1.6216 0.01633 0.00984 -0.2400 0.3351 0.4737
4.500 1.6409 0.01678 0.01027 -0.2388 0.3318 0.4818
4.750 1.6584 0.01734 0.01080 -0.2373 0.3282 0.4885
5.000 1.6767 0.01785 0.01132 -0.2360 0.3253 0.4956
5.250 1.6987 0.01818 0.01168 -0.2352 0.3238 0.5027
5.500 1.7196 0.01856 0.01209 -0.2343 0.3220 0.5080
5.750 1.7396 0.01900 0.01255 -0.2333 0.3201 0.5131
6.000 1.7591 0.01947 0.01305 -0.2323 0.3183 0.5179
6.250 1.7778 0.02000 0.01357 -0.2312 0.3162 0.5222
6.500 1.7949 0.02061 0.01419 -0.2298 0.3140 0.5263
6.750 1.8112 0.02129 0.01487 -0.2284 0.3113 0.5310
7.000 1.8259 0.02207 0.01566 -0.2268 0.3086 0.5355
7.250 1.8448 0.02261 0.01623 -0.2258 0.3075 0.5404
7.500 1.8642 0.02312 0.01679 -0.2249 0.3064 0.5454
7.750 1.8836 0.02364 0.01736 -0.2240 0.3050 0.5515
8.000 1.9019 0.02421 0.01798 -0.2230 0.3034 0.5591
8.250 1.9190 0.02487 0.01868 -0.2219 0.3016 0.5685
8.500 1.9358 0.02556 0.01941 -0.2208 0.2999 0.5785
8.750 1.9517 0.02632 0.02020 -0.2196 0.2981 0.5860
9.000 1.9659 0.02721 0.02113 -0.2182 0.2960 0.5934
9.250 1.9786 0.02821 0.02213 -0.2166 0.2931 0.6015
9.500 1.9934 0.02908 0.02306 -0.2154 0.2907 0.6128
9.750 2.0118 0.02973 0.02378 -0.2146 0.2891 0.6272
10.000 2.0298 0.03040 0.02454 -0.2139 0.2869 0.6471
10.500 2.0600 0.03220 0.02652 -0.2118 0.2807 0.7370
10.750 2.0707 0.03312 0.02768 -0.2102 0.2776 1.0000
11.000 2.0825 0.03431 0.02888 -0.2088 0.2746 1.0000
11.250 2.0989 0.03514 0.02976 -0.2080 0.2728 1.0000
11.500 2.1140 0.03606 0.03071 -0.2070 0.2702 1.0000
11.750 2.1275 0.03712 0.03179 -0.2059 0.2669 1.0000
12.000 2.1366 0.03857 0.03325 -0.2045 0.2630 1.0000
12.250 2.1456 0.04005 0.03472 -0.2031 0.2586 1.0000
12.500 2.1597 0.04109 0.03580 -0.2021 0.2549 1.0000
12.750 2.1689 0.04258 0.03731 -0.2008 0.2498 1.0000
13.000 2.1739 0.04443 0.03914 -0.1992 0.2439 1.0000
13.250 2.1829 0.04595 0.04069 -0.1980 0.2375 1.0000
13.500 2.1840 0.04821 0.04290 -0.1962 0.2278 1.0000
13.750 2.1794 0.05108 0.04572 -0.1940 0.2135 1.0000
14.000 2.1653 0.05491 0.04945 -0.1913 0.1937 1.0000
14.250 2.1464 0.05930 0.05375 -0.1886 0.1770 1.0000
14.500 2.1353 0.06304 0.05747 -0.1865 0.1669 1.0000
14.750 2.1254 0.06674 0.06117 -0.1847 0.1594 1.0000
15.000 2.1193 0.07011 0.06457 -0.1832 0.1543 1.0000
15.250 2.1101 0.07386 0.06835 -0.1817 0.1492 1.0000
15.500 2.1071 0.07696 0.07150 -0.1806 0.1455 1.0000
15.750 2.1016 0.08042 0.07501 -0.1795 0.1420 1.0000
16.000 2.0935 0.08420 0.07883 -0.1784 0.1384 1.0000
16.250 2.0839 0.08820 0.08288 -0.1775 0.1348 1.0000
16.500 2.0802 0.09153 0.08628 -0.1768 0.1324 1.0000
16.750 2.0736 0.09522 0.09002 -0.1761 0.1292 1.0000
17.000 2.0612 0.09975 0.09461 -0.1755 0.1259 1.0000
17.250 2.0479 0.10445 0.09937 -0.1751 0.1229 1.0000
17.500 2.0424 0.10812 0.10312 -0.1749 0.1207 1.0000
17.750 2.0339 0.11221 0.10727 -0.1747 0.1178 1.0000
18.000 2.0203 0.11709 0.11221 -0.1748 0.1150 1.0000
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