GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 200,000 Max Cl/Cd: 64.27 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe244-il-200000-n5.txt Download as CSV file: xf-goe244-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2824 0.09891 0.09445 -0.1284 0.8290 0.0457
-9.500 0.2920 0.09676 0.09231 -0.1294 0.8216 0.0472
-9.250 0.2875 0.09400 0.08952 -0.1332 0.8151 0.0487
-9.000 0.3033 0.09154 0.08702 -0.1329 0.8089 0.0490
-8.750 0.3168 0.08950 0.08498 -0.1329 0.8010 0.0495
-8.500 0.3289 0.08743 0.08288 -0.1334 0.7947 0.0502
-8.250 0.3398 0.08533 0.08076 -0.1343 0.7886 0.0512
-8.000 0.3485 0.08313 0.07856 -0.1356 0.7816 0.0525
-7.750 0.3443 0.07991 0.07530 -0.1401 0.7753 0.0539
-7.500 0.3569 0.07767 0.07305 -0.1403 0.7689 0.0541
-7.250 0.3712 0.07588 0.07126 -0.1400 0.7614 0.0545
-7.000 0.3844 0.07396 0.06929 -0.1403 0.7551 0.0551
-6.750 0.3951 0.07204 0.06738 -0.1409 0.7481 0.0559
-6.250 0.3905 0.06257 0.05783 -0.1481 0.7348 0.0441
-5.750 0.4717 0.02845 0.02253 -0.2169 0.7215 0.0349
-5.500 0.5263 0.02527 0.01878 -0.2272 0.7161 0.0350
-5.250 0.5679 0.02350 0.01664 -0.2324 0.7095 0.0353
-5.000 0.6010 0.02252 0.01557 -0.2344 0.7025 0.0358
-4.750 0.6356 0.02170 0.01459 -0.2364 0.6962 0.0364
-4.500 0.6680 0.02092 0.01367 -0.2381 0.6887 0.0369
-4.250 0.7016 0.02015 0.01271 -0.2397 0.6816 0.0371
-4.000 0.7347 0.01950 0.01190 -0.2410 0.6751 0.0373
-3.750 0.7652 0.01899 0.01129 -0.2418 0.6673 0.0376
-3.500 0.7966 0.01855 0.01071 -0.2426 0.6595 0.0380
-3.250 0.8263 0.01820 0.01029 -0.2431 0.6510 0.0383
-3.000 0.8562 0.01791 0.00990 -0.2436 0.6418 0.0388
-2.750 0.8856 0.01768 0.00960 -0.2440 0.6326 0.0392
-2.500 0.9150 0.01747 0.00933 -0.2445 0.6227 0.0397
-2.250 0.9445 0.01731 0.00914 -0.2450 0.6129 0.0404
-2.000 0.9733 0.01721 0.00897 -0.2453 0.6020 0.0414
-1.750 1.0013 0.01716 0.00885 -0.2455 0.5905 0.0430
-1.500 1.0287 0.01715 0.00873 -0.2456 0.5782 0.0445
-1.250 1.0549 0.01718 0.00866 -0.2454 0.5637 0.0460
-1.000 1.0797 0.01727 0.00864 -0.2449 0.5477 0.0476
-0.750 1.1030 0.01742 0.00867 -0.2442 0.5300 0.0497
-0.500 1.1245 0.01764 0.00877 -0.2431 0.5112 0.0534
-0.250 1.1445 0.01792 0.00895 -0.2418 0.4931 0.0624
0.000 1.1629 0.01824 0.00915 -0.2402 0.4773 0.0788
0.250 1.1823 0.01845 0.00936 -0.2391 0.4640 0.1165
0.500 1.2018 0.01870 0.00979 -0.2381 0.4524 0.2265
0.750 1.2208 0.01913 0.01016 -0.2367 0.4430 0.2486
1.000 1.2401 0.01959 0.01055 -0.2354 0.4344 0.2659
1.250 1.2594 0.02007 0.01098 -0.2341 0.4273 0.2823
1.500 1.2805 0.02048 0.01139 -0.2332 0.4207 0.3037
1.750 1.3004 0.02095 0.01185 -0.2320 0.4146 0.3245
2.000 1.3194 0.02148 0.01236 -0.2308 0.4094 0.3475
2.250 1.3409 0.02189 0.01282 -0.2299 0.4045 0.3739
2.500 1.3610 0.02237 0.01332 -0.2288 0.3995 0.3976
2.750 1.3802 0.02291 0.01384 -0.2276 0.3949 0.4177
3.000 1.3988 0.02351 0.01437 -0.2263 0.3908 0.4355
3.250 1.4190 0.02401 0.01488 -0.2252 0.3873 0.4524
3.500 1.4395 0.02449 0.01538 -0.2242 0.3838 0.4678
3.750 1.4595 0.02501 0.01590 -0.2232 0.3804 0.4816
4.000 1.4790 0.02557 0.01643 -0.2221 0.3772 0.4932
4.250 1.4981 0.02615 0.01698 -0.2209 0.3742 0.5025
4.500 1.5173 0.02675 0.01753 -0.2198 0.3715 0.5119
4.750 1.5374 0.02731 0.01806 -0.2189 0.3690 0.5202
5.000 1.5575 0.02783 0.01863 -0.2180 0.3666 0.5283
5.250 1.5772 0.02839 0.01922 -0.2170 0.3642 0.5368
5.500 1.5964 0.02896 0.01984 -0.2160 0.3617 0.5445
5.750 1.6153 0.02957 0.02045 -0.2150 0.3594 0.5533
6.000 1.6341 0.03019 0.02109 -0.2140 0.3571 0.5612
6.250 1.6525 0.03083 0.02173 -0.2129 0.3548 0.5703
6.500 1.6711 0.03148 0.02236 -0.2119 0.3525 0.5793
6.750 1.6902 0.03211 0.02297 -0.2109 0.3500 0.5897
7.000 1.7060 0.03286 0.02382 -0.2097 0.3475 0.6005
7.250 1.7216 0.03362 0.02466 -0.2084 0.3447 0.6128
7.500 1.7365 0.03443 0.02555 -0.2070 0.3417 0.6239
7.750 1.7510 0.03527 0.02643 -0.2057 0.3387 0.6341
8.000 1.7659 0.03609 0.02728 -0.2044 0.3359 0.6429
8.500 1.7985 0.03764 0.02879 -0.2021 0.3309 0.6659
8.750 1.8124 0.03856 0.02985 -0.2009 0.3290 0.6793
9.000 1.8264 0.03948 0.03089 -0.1996 0.3268 0.6969
9.250 1.8398 0.04043 0.03197 -0.1983 0.3245 0.7236
9.500 1.8527 0.04130 0.03303 -0.1970 0.3223 0.7909
9.750 1.8609 0.04226 0.03409 -0.1950 0.3198 1.0000
10.000 1.8727 0.04342 0.03525 -0.1938 0.3171 1.0000
10.250 1.8857 0.04449 0.03630 -0.1926 0.3147 1.0000
10.500 1.9012 0.04539 0.03716 -0.1916 0.3126 1.0000
10.750 1.9121 0.04669 0.03857 -0.1904 0.3107 1.0000
11.000 1.9214 0.04813 0.04012 -0.1891 0.3084 1.0000
11.250 1.9299 0.04965 0.04173 -0.1877 0.3056 1.0000
11.500 1.9372 0.05128 0.04344 -0.1864 0.3026 1.0000
11.750 1.9456 0.05282 0.04503 -0.1852 0.2997 1.0000
12.000 1.9547 0.05429 0.04652 -0.1840 0.2970 1.0000
12.250 1.9661 0.05556 0.04776 -0.1829 0.2946 1.0000
12.500 1.9715 0.05752 0.04987 -0.1817 0.2922 1.0000
12.750 1.9760 0.05958 0.05208 -0.1805 0.2894 1.0000
13.000 1.9807 0.06164 0.05425 -0.1793 0.2865 1.0000
13.250 1.9847 0.06378 0.05648 -0.1782 0.2833 1.0000
13.500 1.9894 0.06583 0.05855 -0.1772 0.2799 1.0000
13.750 1.9928 0.06807 0.06084 -0.1761 0.2765 1.0000
14.000 1.9900 0.07118 0.06414 -0.1751 0.2720 1.0000
14.250 1.9879 0.07420 0.06726 -0.1741 0.2671 1.0000
14.500 1.9869 0.07705 0.07013 -0.1733 0.2625 1.0000
14.750 1.9819 0.08057 0.07380 -0.1725 0.2574 1.0000
15.000 1.9754 0.08432 0.07768 -0.1718 0.2515 1.0000
15.250 1.9695 0.08798 0.08137 -0.1712 0.2458 1.0000
15.500 1.9581 0.09255 0.08611 -0.1707 0.2385 1.0000
15.750 1.9458 0.09721 0.09082 -0.1704 0.2310 1.0000
16.000 1.9300 0.10248 0.09621 -0.1703 0.2218 1.0000
16.250 1.9121 0.10809 0.10189 -0.1704 0.2120 1.0000
16.500 1.8908 0.11431 0.10813 -0.1709 0.2017 1.0000
16.750 1.8673 0.12095 0.11480 -0.1717 0.1919 1.0000
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