GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 500,000 Max Cl/Cd: 110.6 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe234-il-500000.txt Download as CSV file: xf-goe234-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0367 0.08363 0.08091 -0.1025 0.8796 0.0439
-9.000 -0.0968 0.06268 0.05985 -0.1149 0.8706 0.0380
-8.750 -0.1119 0.03447 0.03083 -0.1684 0.8584 0.0368
-8.500 -0.0383 0.02606 0.02173 -0.1960 0.8542 0.0378
-8.250 -0.0029 0.02412 0.01969 -0.2004 0.8494 0.0386
-8.000 0.0328 0.02295 0.01846 -0.2040 0.8448 0.0394
-7.750 0.0690 0.02188 0.01727 -0.2074 0.8403 0.0404
-7.500 0.1073 0.02053 0.01575 -0.2115 0.8358 0.0415
-7.250 0.1441 0.01936 0.01442 -0.2148 0.8311 0.0423
-7.000 0.1802 0.01843 0.01332 -0.2176 0.8264 0.0431
-6.750 0.2126 0.01766 0.01241 -0.2189 0.8219 0.0440
-6.500 0.2421 0.01724 0.01203 -0.2193 0.8171 0.0452
-6.250 0.2744 0.01679 0.01155 -0.2206 0.8119 0.0463
-6.000 0.3065 0.01640 0.01109 -0.2216 0.8072 0.0473
-5.750 0.3384 0.01610 0.01070 -0.2226 0.8025 0.0485
-5.500 0.3708 0.01574 0.01031 -0.2237 0.7972 0.0497
-5.250 0.4025 0.01546 0.00998 -0.2245 0.7918 0.0511
-5.000 0.4339 0.01526 0.00976 -0.2253 0.7869 0.0530
-4.750 0.4670 0.01494 0.00943 -0.2266 0.7817 0.0549
-4.500 0.5001 0.01460 0.00905 -0.2280 0.7759 0.0570
-4.250 0.5330 0.01429 0.00865 -0.2292 0.7704 0.0587
-4.000 0.5688 0.01377 0.00811 -0.2315 0.7648 0.0627
-3.750 0.6036 0.01325 0.00754 -0.2334 0.7585 0.0667
-3.500 0.6414 0.01237 0.00653 -0.2365 0.7528 0.0725
-3.250 0.6771 0.01163 0.00566 -0.2388 0.7467 0.0797
-3.000 0.7187 0.00998 0.00423 -0.2435 0.7398 0.2054
-2.750 0.7480 0.01004 0.00436 -0.2436 0.7334 0.2683
-2.500 0.7770 0.01017 0.00446 -0.2435 0.7261 0.2814
-2.250 0.8048 0.01046 0.00477 -0.2430 0.7181 0.2885
-2.000 0.8334 0.01064 0.00487 -0.2429 0.7095 0.2955
-1.750 0.8611 0.01087 0.00509 -0.2425 0.7006 0.2996
-1.500 0.8883 0.01123 0.00549 -0.2419 0.6920 0.3029
-1.250 0.9157 0.01153 0.00575 -0.2414 0.6834 0.3068
-1.000 0.9447 0.01163 0.00577 -0.2415 0.6747 0.3111
-0.750 0.9725 0.01180 0.00587 -0.2413 0.6655 0.3139
-0.500 0.9996 0.01205 0.00615 -0.2408 0.6549 0.3155
-0.250 1.0258 0.01242 0.00649 -0.2400 0.6451 0.3172
0.000 1.0515 0.01285 0.00698 -0.2391 0.6363 0.3192
0.250 1.0787 0.01308 0.00716 -0.2388 0.6292 0.3213
0.500 1.1087 0.01297 0.00700 -0.2393 0.6220 0.3243
0.750 1.1393 0.01285 0.00671 -0.2401 0.6151 0.3281
1.000 1.1682 0.01279 0.00662 -0.2404 0.6088 0.3297
1.250 1.1964 0.01283 0.00666 -0.2404 0.6019 0.3307
1.500 1.2237 0.01298 0.00677 -0.2402 0.5955 0.3318
1.750 1.2514 0.01309 0.00691 -0.2401 0.5891 0.3332
2.000 1.2787 0.01323 0.00705 -0.2399 0.5823 0.3346
2.250 1.3063 0.01333 0.00711 -0.2398 0.5760 0.3359
2.500 1.3346 0.01333 0.00711 -0.2399 0.5691 0.3375
2.750 1.3623 0.01338 0.00711 -0.2400 0.5622 0.3393
3.000 1.3904 0.01339 0.00709 -0.2401 0.5555 0.3414
3.250 1.4181 0.01345 0.00710 -0.2401 0.5479 0.3438
3.500 1.4452 0.01354 0.00713 -0.2400 0.5408 0.3455
3.750 1.4723 0.01356 0.00718 -0.2399 0.5328 0.3469
4.000 1.4979 0.01372 0.00732 -0.2395 0.5247 0.3480
4.250 1.5240 0.01383 0.00746 -0.2392 0.5150 0.3492
4.500 1.5488 0.01402 0.00763 -0.2386 0.5041 0.3505
4.750 1.5729 0.01424 0.00782 -0.2379 0.4918 0.3520
5.000 1.5971 0.01444 0.00800 -0.2372 0.4781 0.3536
5.250 1.6201 0.01470 0.00822 -0.2363 0.4625 0.3554
5.500 1.6421 0.01500 0.00846 -0.2353 0.4459 0.3573
5.750 1.6629 0.01536 0.00874 -0.2341 0.4280 0.3593
6.000 1.6817 0.01582 0.00910 -0.2325 0.4083 0.3609
6.250 1.6987 0.01633 0.00950 -0.2306 0.3867 0.3626
6.500 1.7132 0.01691 0.00999 -0.2282 0.3647 0.3642
6.750 1.7249 0.01759 0.01058 -0.2254 0.3448 0.3655
7.000 1.7313 0.01829 0.01122 -0.2215 0.3280 0.3667
7.250 1.7408 0.01902 0.01190 -0.2183 0.3138 0.3681
7.500 1.7527 0.01978 0.01263 -0.2157 0.3019 0.3696
7.750 1.7647 0.02058 0.01339 -0.2132 0.2911 0.3713
8.000 1.7791 0.02128 0.01408 -0.2112 0.2822 0.3730
8.500 1.8052 0.02287 0.01567 -0.2069 0.2662 0.3766
8.750 1.8168 0.02380 0.01657 -0.2046 0.2590 0.3779
9.000 1.8309 0.02457 0.01738 -0.2028 0.2529 0.3796
9.250 1.8438 0.02544 0.01830 -0.2009 0.2461 0.3813
9.500 1.8536 0.02656 0.01942 -0.1986 0.2391 0.3829
9.750 1.8675 0.02742 0.02034 -0.1969 0.2324 0.3849
10.000 1.8754 0.02874 0.02165 -0.1945 0.2245 0.3868
10.250 1.8880 0.02975 0.02271 -0.1928 0.2162 0.3887
10.500 1.8952 0.03121 0.02415 -0.1906 0.2064 0.3904
10.750 1.9010 0.03283 0.02572 -0.1883 0.1921 0.3919
11.000 1.9032 0.03479 0.02759 -0.1858 0.1674 0.3933
11.250 1.8779 0.03920 0.03161 -0.1809 0.1157 0.3936
11.500 1.8589 0.04327 0.03552 -0.1770 0.0881 0.3942
11.750 1.8377 0.04783 0.03990 -0.1734 0.0540 0.3948
12.000 1.8282 0.05142 0.04345 -0.1709 0.0423 0.3959
12.250 1.8268 0.05426 0.04636 -0.1691 0.0392 0.3971
12.500 1.8251 0.05723 0.04940 -0.1674 0.0369 0.3984
12.750 1.8264 0.05994 0.05221 -0.1661 0.0356 0.3998
13.000 1.8261 0.06288 0.05526 -0.1647 0.0345 0.4014
13.250 1.8238 0.06614 0.05862 -0.1635 0.0334 0.4031
13.500 1.8187 0.06980 0.06237 -0.1623 0.0324 0.4046
13.750 1.8109 0.07393 0.06661 -0.1612 0.0314 0.4060
14.000 1.8057 0.07781 0.07060 -0.1603 0.0307 0.4074
14.250 1.8036 0.08128 0.07419 -0.1595 0.0301 0.4087
14.500 1.7997 0.08505 0.07807 -0.1589 0.0295 0.4097
14.750 1.7945 0.08908 0.08222 -0.1585 0.0289 0.4111
15.000 1.7879 0.09338 0.08663 -0.1582 0.0283 0.4124
15.250 1.7801 0.09788 0.09124 -0.1580 0.0277 0.4135
15.500 1.7701 0.10275 0.09622 -0.1580 0.0272 0.4146
15.750 1.7576 0.10805 0.10163 -0.1582 0.0267 0.4156
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