GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 500,000 Max Cl/Cd: 92.31 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe244-il-500000.txt Download as CSV file: xf-goe244-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.2424 0.10246 0.09939 -0.1226 0.8420 0.0312
-10.250 0.2522 0.10000 0.09690 -0.1239 0.8359 0.0320
-10.000 0.2440 0.09554 0.09238 -0.1294 0.8303 0.0334
-9.750 0.2563 0.09287 0.08971 -0.1298 0.8247 0.0336
-9.500 0.2718 0.09088 0.08772 -0.1298 0.8187 0.0338
-9.250 0.2858 0.08898 0.08576 -0.1301 0.8129 0.0340
-9.000 0.2987 0.08702 0.08379 -0.1308 0.8068 0.0343
-8.750 0.3108 0.08498 0.08175 -0.1318 0.8004 0.0348
-8.500 0.3223 0.08282 0.07955 -0.1329 0.7949 0.0354
-8.250 0.3330 0.08049 0.07719 -0.1344 0.7894 0.0363
-8.000 0.3263 0.07495 0.07166 -0.1410 0.7829 0.0380
-7.750 0.3414 0.07332 0.06999 -0.1407 0.7767 0.0382
-7.500 0.3567 0.07181 0.06845 -0.1409 0.7705 0.0385
-7.250 0.3713 0.07020 0.06685 -0.1414 0.7635 0.0389
-7.000 0.3848 0.06843 0.06503 -0.1423 0.7570 0.0396
-6.750 0.3769 0.06210 0.05872 -0.1508 0.7505 0.0428
-6.500 0.3925 0.06082 0.05744 -0.1502 0.7442 0.0431
-6.250 0.4092 0.05958 0.05615 -0.1503 0.7385 0.0434
-6.000 0.4255 0.05114 0.04769 -0.1670 0.7327 0.0480
-5.750 0.4412 0.05059 0.04716 -0.1651 0.7265 0.0483
-5.500 0.4598 0.04982 0.04635 -0.1647 0.7205 0.0486
-5.250 0.4796 0.04881 0.04532 -0.1653 0.7146 0.0491
-5.000 0.5007 0.04727 0.04378 -0.1673 0.7078 0.0501
-4.750 0.6781 0.01801 0.01260 -0.2458 0.7016 0.0438
-4.500 0.7148 0.01636 0.01070 -0.2482 0.6953 0.0407
-4.250 0.7511 0.01505 0.00910 -0.2503 0.6884 0.0394
-4.000 0.7834 0.01443 0.00831 -0.2513 0.6817 0.0392
-3.750 0.8146 0.01396 0.00777 -0.2520 0.6750 0.0393
-3.500 0.8453 0.01358 0.00733 -0.2526 0.6674 0.0395
-3.250 0.8757 0.01329 0.00695 -0.2531 0.6603 0.0397
-3.000 0.9061 0.01301 0.00665 -0.2536 0.6522 0.0400
-2.750 0.9358 0.01283 0.00638 -0.2540 0.6436 0.0404
-2.500 0.9657 0.01264 0.00617 -0.2544 0.6347 0.0409
-2.250 0.9946 0.01255 0.00600 -0.2546 0.6247 0.0418
-2.000 1.0238 0.01245 0.00586 -0.2549 0.6145 0.0425
-1.750 1.0525 0.01238 0.00569 -0.2551 0.6035 0.0431
-1.500 1.0814 0.01228 0.00555 -0.2554 0.5909 0.0441
-1.250 1.1088 0.01230 0.00549 -0.2553 0.5771 0.0453
-1.000 1.1344 0.01239 0.00547 -0.2549 0.5607 0.0468
-0.750 1.1585 0.01255 0.00551 -0.2543 0.5407 0.0488
-0.500 1.1803 0.01280 0.00564 -0.2532 0.5166 0.0525
-0.250 1.1997 0.01316 0.00587 -0.2517 0.4918 0.0636
0.000 1.2197 0.01349 0.00610 -0.2503 0.4704 0.0900
0.250 1.2424 0.01364 0.00642 -0.2499 0.4536 0.2154
0.500 1.2602 0.01400 0.00674 -0.2481 0.4408 0.2417
0.750 1.2784 0.01434 0.00705 -0.2464 0.4311 0.2613
1.000 1.2971 0.01475 0.00740 -0.2449 0.4222 0.2768
1.250 1.3182 0.01511 0.00774 -0.2438 0.4150 0.2934
1.500 1.3401 0.01544 0.00807 -0.2429 0.4086 0.3094
1.750 1.3601 0.01586 0.00847 -0.2416 0.4027 0.3282
2.000 1.3812 0.01624 0.00887 -0.2406 0.3977 0.3535
2.250 1.4038 0.01654 0.00923 -0.2399 0.3934 0.3828
2.500 1.4247 0.01693 0.00966 -0.2388 0.3890 0.4153
2.750 1.4438 0.01742 0.01013 -0.2374 0.3849 0.4398
3.000 1.4615 0.01800 0.01068 -0.2359 0.3805 0.4554
3.250 1.4835 0.01834 0.01104 -0.2350 0.3779 0.4690
3.500 1.5048 0.01872 0.01144 -0.2340 0.3749 0.4815
3.750 1.5251 0.01915 0.01189 -0.2329 0.3719 0.4928
4.000 1.5442 0.01966 0.01236 -0.2317 0.3689 0.5036
4.250 1.5629 0.02019 0.01289 -0.2304 0.3660 0.5123
4.500 1.5812 0.02079 0.01344 -0.2291 0.3626 0.5213
4.750 1.6017 0.02123 0.01392 -0.2281 0.3606 0.5292
5.000 1.6218 0.02167 0.01440 -0.2271 0.3583 0.5362
5.250 1.6413 0.02215 0.01489 -0.2261 0.3554 0.5429
5.500 1.6602 0.02266 0.01542 -0.2250 0.3521 0.5489
5.750 1.6777 0.02327 0.01602 -0.2237 0.3491 0.5551
6.000 1.6947 0.02394 0.01666 -0.2223 0.3461 0.5612
6.250 1.7133 0.02454 0.01725 -0.2212 0.3431 0.5672
6.500 1.7321 0.02506 0.01785 -0.2202 0.3413 0.5739
6.750 1.7503 0.02564 0.01847 -0.2191 0.3391 0.5809
7.000 1.7685 0.02622 0.01910 -0.2181 0.3370 0.5871
7.250 1.7866 0.02682 0.01975 -0.2170 0.3350 0.5945
7.500 1.8041 0.02747 0.02042 -0.2159 0.3331 0.6031
7.750 1.8209 0.02816 0.02115 -0.2147 0.3312 0.6139
8.000 1.8373 0.02889 0.02189 -0.2135 0.3290 0.6252
8.250 1.8550 0.02955 0.02255 -0.2124 0.3263 0.6364
8.500 1.8721 0.03023 0.02331 -0.2114 0.3245 0.6461
8.750 1.8878 0.03100 0.02416 -0.2102 0.3227 0.6572
9.000 1.9042 0.03175 0.02500 -0.2092 0.3209 0.6711
9.250 1.9208 0.03249 0.02584 -0.2082 0.3189 0.6908
9.500 1.9367 0.03329 0.02675 -0.2072 0.3169 0.7226
9.750 1.9489 0.03386 0.02757 -0.2055 0.3150 1.0000
10.000 1.9640 0.03475 0.02845 -0.2044 0.3130 1.0000
10.250 1.9787 0.03565 0.02934 -0.2032 0.3108 1.0000
10.500 1.9947 0.03645 0.03011 -0.2021 0.3080 1.0000
10.750 2.0070 0.03759 0.03133 -0.2010 0.3063 1.0000
11.000 2.0197 0.03871 0.03253 -0.1998 0.3039 1.0000
11.250 2.0311 0.03996 0.03384 -0.1987 0.3010 1.0000
11.500 2.0425 0.04121 0.03511 -0.1975 0.2981 1.0000
11.750 2.0524 0.04258 0.03649 -0.1962 0.2951 1.0000
12.000 2.0628 0.04386 0.03773 -0.1948 0.2917 1.0000
12.250 2.0740 0.04521 0.03919 -0.1938 0.2894 1.0000
12.500 2.0841 0.04670 0.04076 -0.1928 0.2864 1.0000
12.750 2.0944 0.04815 0.04228 -0.1917 0.2833 1.0000
13.000 2.1028 0.04978 0.04394 -0.1906 0.2801 1.0000
13.250 2.1085 0.05164 0.04580 -0.1892 0.2764 1.0000
13.500 2.1165 0.05335 0.04758 -0.1882 0.2729 1.0000
13.750 2.1251 0.05508 0.04940 -0.1873 0.2688 1.0000
14.000 2.1305 0.05710 0.05146 -0.1862 0.2641 1.0000
14.250 2.1312 0.05961 0.05397 -0.1848 0.2595 1.0000
14.500 2.1393 0.06142 0.05589 -0.1840 0.2548 1.0000
14.750 2.1416 0.06386 0.05838 -0.1829 0.2486 1.0000
15.000 2.1396 0.06676 0.06130 -0.1817 0.2423 1.0000
15.250 2.1388 0.06959 0.06417 -0.1806 0.2332 1.0000
15.500 2.1314 0.07318 0.06778 -0.1794 0.2229 1.0000
15.750 2.1161 0.07778 0.07236 -0.1779 0.2096 1.0000
16.000 2.0937 0.08328 0.07783 -0.1765 0.1953 1.0000
16.250 2.0683 0.08925 0.08379 -0.1752 0.1837 1.0000
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