GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 500,000 Max Cl/Cd: 79.5 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe244-il-500000-n5.txt Download as CSV file: xf-goe244-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.2218 0.10295 0.09947 -0.1210 0.7908 0.0273
-10.500 0.2269 0.09961 0.09612 -0.1233 0.7846 0.0273
-10.250 0.2342 0.09658 0.09305 -0.1251 0.7778 0.0274
-10.000 0.2421 0.09359 0.09001 -0.1268 0.7713 0.0274
-9.750 0.2515 0.09081 0.08723 -0.1283 0.7644 0.0275
-9.500 0.2648 0.08897 0.08535 -0.1287 0.7573 0.0276
-9.250 0.2785 0.08716 0.08351 -0.1293 0.7514 0.0278
-9.000 0.2918 0.08528 0.08163 -0.1301 0.7454 0.0280
-8.750 0.3037 0.08322 0.07955 -0.1312 0.7391 0.0282
-7.750 0.3336 0.07062 0.06683 -0.1393 0.7126 0.0272
-6.750 0.3932 0.02264 0.01770 -0.2228 0.6877 0.0253
-6.500 0.4383 0.02057 0.01528 -0.2301 0.6785 0.0255
-6.250 0.4781 0.01918 0.01365 -0.2347 0.6715 0.0257
-6.000 0.5150 0.01815 0.01240 -0.2378 0.6646 0.0259
-5.500 0.5839 0.01665 0.01055 -0.2421 0.6509 0.0263
-5.250 0.6165 0.01610 0.00985 -0.2435 0.6427 0.0265
-5.000 0.6485 0.01564 0.00924 -0.2447 0.6350 0.0267
-4.750 0.6800 0.01524 0.00872 -0.2457 0.6264 0.0269
-4.500 0.7106 0.01494 0.00828 -0.2465 0.6185 0.0270
-4.250 0.7416 0.01468 0.00793 -0.2472 0.6105 0.0273
-4.000 0.7715 0.01441 0.00756 -0.2478 0.6014 0.0276
-3.750 0.8019 0.01408 0.00721 -0.2485 0.5926 0.0279
-3.500 0.8310 0.01390 0.00697 -0.2489 0.5820 0.0282
-3.250 0.8604 0.01374 0.00675 -0.2494 0.5703 0.0285
-3.000 0.8883 0.01367 0.00659 -0.2495 0.5562 0.0287
-2.750 0.9153 0.01365 0.00647 -0.2495 0.5386 0.0290
-2.500 0.9410 0.01371 0.00640 -0.2492 0.5170 0.0293
-2.250 0.9651 0.01386 0.00639 -0.2487 0.4925 0.0297
-2.000 0.9882 0.01406 0.00643 -0.2479 0.4701 0.0300
-1.750 1.0119 0.01425 0.00649 -0.2473 0.4521 0.0304
-1.500 1.0360 0.01442 0.00656 -0.2468 0.4384 0.0307
-1.250 1.0596 0.01461 0.00665 -0.2461 0.4272 0.0311
-1.000 1.0851 0.01471 0.00669 -0.2458 0.4180 0.0316
-0.500 1.1308 0.01500 0.00687 -0.2441 0.4036 0.0328
-0.250 1.1530 0.01517 0.00700 -0.2432 0.3974 0.0338
0.000 1.1738 0.01543 0.00718 -0.2420 0.3913 0.0349
0.250 1.1981 0.01561 0.00733 -0.2414 0.3864 0.0361
0.500 1.2225 0.01581 0.00751 -0.2409 0.3813 0.0376
0.750 1.2457 0.01608 0.00773 -0.2402 0.3761 0.0398
1.000 1.2690 0.01635 0.00803 -0.2396 0.3712 0.0661
1.250 1.2924 0.01660 0.00829 -0.2390 0.3677 0.0808
1.500 1.3172 0.01679 0.00852 -0.2387 0.3643 0.1030
1.750 1.3436 0.01690 0.00886 -0.2389 0.3607 0.2131
2.000 1.3656 0.01722 0.00921 -0.2381 0.3572 0.2335
2.250 1.3865 0.01761 0.00960 -0.2371 0.3538 0.2497
2.500 1.4068 0.01804 0.01001 -0.2360 0.3505 0.2635
2.750 1.4295 0.01834 0.01036 -0.2354 0.3483 0.2821
3.000 1.4519 0.01866 0.01074 -0.2347 0.3459 0.3068
3.250 1.4739 0.01900 0.01117 -0.2340 0.3434 0.3401
3.500 1.4951 0.01939 0.01164 -0.2331 0.3409 0.3780
3.750 1.5152 0.01984 0.01214 -0.2321 0.3384 0.4071
4.000 1.5342 0.02036 0.01267 -0.2309 0.3360 0.4250
4.250 1.5525 0.02092 0.01322 -0.2297 0.3336 0.4384
4.500 1.5705 0.02151 0.01382 -0.2284 0.3312 0.4504
4.750 1.5907 0.02198 0.01432 -0.2274 0.3296 0.4622
5.000 1.6105 0.02247 0.01484 -0.2264 0.3276 0.4731
5.250 1.6297 0.02300 0.01539 -0.2254 0.3247 0.4811
5.500 1.6480 0.02359 0.01599 -0.2242 0.3215 0.4885
5.750 1.6648 0.02428 0.01667 -0.2229 0.3185 0.4947
6.000 1.6812 0.02500 0.01739 -0.2216 0.3158 0.4997
6.250 1.6966 0.02578 0.01818 -0.2202 0.3130 0.5046
6.500 1.7146 0.02642 0.01885 -0.2191 0.3110 0.5098
6.750 1.7329 0.02704 0.01951 -0.2181 0.3090 0.5146
7.000 1.7507 0.02769 0.02020 -0.2171 0.3068 0.5191
7.250 1.7678 0.02840 0.02095 -0.2160 0.3050 0.5245
7.500 1.7841 0.02917 0.02176 -0.2148 0.3032 0.5320
7.750 1.8000 0.02996 0.02259 -0.2136 0.3014 0.5415
8.000 1.8154 0.03080 0.02347 -0.2124 0.2996 0.5524
8.250 1.8296 0.03174 0.02444 -0.2111 0.2977 0.5604
8.500 1.8434 0.03274 0.02547 -0.2097 0.2956 0.5673
8.750 1.8588 0.03362 0.02639 -0.2086 0.2938 0.5735
9.000 1.8755 0.03443 0.02727 -0.2077 0.2921 0.5797
9.250 1.8914 0.03529 0.02820 -0.2067 0.2901 0.5866
9.500 1.9068 0.03621 0.02917 -0.2057 0.2878 0.5943
9.750 1.9212 0.03721 0.03023 -0.2046 0.2856 0.6030
10.000 1.9344 0.03833 0.03140 -0.2035 0.2833 0.6144
10.250 1.9473 0.03948 0.03261 -0.2023 0.2811 0.6287
10.500 1.9591 0.04074 0.03392 -0.2011 0.2790 0.6459
10.750 1.9715 0.04197 0.03523 -0.2000 0.2770 0.6680
11.000 1.9868 0.04296 0.03634 -0.1992 0.2742 0.7014
11.250 2.0002 0.04404 0.03763 -0.1983 0.2700 0.8138
11.500 2.0057 0.04549 0.03915 -0.1964 0.2657 1.0000
11.750 2.0129 0.04724 0.04089 -0.1951 0.2618 1.0000
12.000 2.0246 0.04859 0.04230 -0.1941 0.2582 1.0000
12.250 2.0347 0.05011 0.04386 -0.1930 0.2535 1.0000
12.500 2.0396 0.05215 0.04590 -0.1917 0.2479 1.0000
12.750 2.0468 0.05397 0.04776 -0.1905 0.2426 1.0000
13.000 2.0506 0.05616 0.04995 -0.1892 0.2346 1.0000
13.250 2.0511 0.05872 0.05252 -0.1878 0.2251 1.0000
13.500 2.0444 0.06213 0.05588 -0.1861 0.2108 1.0000
13.750 2.0292 0.06651 0.06019 -0.1841 0.1930 1.0000
14.000 2.0111 0.07129 0.06492 -0.1821 0.1785 1.0000
14.250 1.9980 0.07561 0.06923 -0.1806 0.1690 1.0000
14.500 1.9853 0.07998 0.07362 -0.1792 0.1618 1.0000
14.750 1.9769 0.08391 0.07761 -0.1782 0.1567 1.0000
15.000 1.9666 0.08812 0.08187 -0.1772 0.1522 1.0000
15.250 1.9578 0.09220 0.08601 -0.1765 0.1485 1.0000
15.500 1.9520 0.09596 0.08984 -0.1759 0.1454 1.0000
15.750 1.9445 0.09997 0.09393 -0.1754 0.1424 1.0000
16.000 1.9351 0.10427 0.09830 -0.1751 0.1394 1.0000
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