BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 50,000 Max Cl/Cd: 27.1 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43015-il-50000-n5.txt Download as CSV file: xf-v43015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43015-2.48 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5223 0.07582 0.06844 -0.0373 1.0000 0.0811
-8.750 -0.5276 0.07307 0.06570 -0.0347 1.0000 0.0801
-8.500 -0.5375 0.07049 0.06309 -0.0316 1.0000 0.0790
-8.250 -0.5495 0.06792 0.06043 -0.0280 1.0000 0.0778
-8.000 -0.5620 0.06538 0.05774 -0.0242 1.0000 0.0761
-7.750 -0.5863 0.06313 0.05495 -0.0184 1.0000 0.0730
-7.500 -0.5837 0.06073 0.05251 -0.0157 1.0000 0.0724
-7.250 -0.5834 0.05848 0.05016 -0.0126 1.0000 0.0718
-7.000 -0.5831 0.05633 0.04786 -0.0094 1.0000 0.0713
-6.750 -0.5817 0.05430 0.04565 -0.0062 1.0000 0.0708
-6.500 -0.5795 0.05242 0.04356 -0.0030 1.0000 0.0709
-6.250 -0.5745 0.05063 0.04151 -0.0002 0.9995 0.0712
-6.000 -0.5439 0.04821 0.03864 -0.0019 0.9892 0.0720
-5.750 -0.5118 0.04595 0.03596 -0.0034 0.9787 0.0723
-5.500 -0.4767 0.04381 0.03348 -0.0053 0.9683 0.0722
-5.250 -0.4408 0.04184 0.03119 -0.0069 0.9572 0.0723
-5.000 -0.4065 0.04017 0.02917 -0.0080 0.9447 0.0728
-4.750 -0.3701 0.03845 0.02733 -0.0097 0.9327 0.0743
-4.500 -0.3260 0.03682 0.02558 -0.0125 0.9224 0.0764
-4.250 -0.2903 0.03546 0.02406 -0.0135 0.9082 0.0776
-4.000 -0.2503 0.03414 0.02261 -0.0151 0.8950 0.0786
-3.750 -0.1990 0.03279 0.02112 -0.0184 0.8851 0.0807
-3.500 -0.1572 0.03160 0.01997 -0.0202 0.8708 0.0836
-3.250 -0.1126 0.03045 0.01890 -0.0224 0.8569 0.0870
-3.000 -0.0675 0.02942 0.01783 -0.0244 0.8434 0.0899
-2.750 -0.0263 0.02835 0.01673 -0.0260 0.8290 0.0940
-2.500 0.0040 0.02748 0.01583 -0.0258 0.8108 0.0993
-2.250 0.0334 0.02667 0.01493 -0.0254 0.7917 0.1045
-2.000 0.0616 0.02582 0.01402 -0.0248 0.7718 0.1116
-1.750 0.0899 0.02500 0.01310 -0.0242 0.7503 0.1221
-1.500 0.1139 0.02424 0.01234 -0.0229 0.7262 0.1393
-1.250 0.1196 0.02201 0.01179 -0.0190 0.7052 0.4703
-1.000 0.1988 0.02202 0.01297 -0.0222 0.6741 0.8460
-0.750 0.2882 0.02313 0.01358 -0.0296 0.6355 0.9137
-0.500 0.3621 0.02361 0.01361 -0.0366 0.5989 0.9504
-0.250 0.4080 0.02368 0.01333 -0.0398 0.5695 0.9665
0.000 0.4457 0.02368 0.01305 -0.0419 0.5429 0.9766
0.250 0.4837 0.02370 0.01278 -0.0442 0.5191 0.9866
0.500 0.5225 0.02373 0.01252 -0.0467 0.4969 0.9961
0.750 0.5484 0.02385 0.01244 -0.0469 0.4784 1.0000
1.000 0.5645 0.02404 0.01248 -0.0451 0.4627 1.0000
1.250 0.5809 0.02425 0.01256 -0.0435 0.4485 1.0000
1.500 0.5981 0.02449 0.01262 -0.0418 0.4361 1.0000
1.750 0.6147 0.02476 0.01277 -0.0401 0.4233 1.0000
2.000 0.6316 0.02506 0.01298 -0.0384 0.4117 1.0000
2.250 0.6493 0.02538 0.01313 -0.0368 0.4015 1.0000
2.500 0.6658 0.02576 0.01347 -0.0350 0.3910 1.0000
2.750 0.6841 0.02613 0.01369 -0.0335 0.3824 1.0000
3.000 0.7005 0.02659 0.01414 -0.0317 0.3731 1.0000
3.250 0.7184 0.02701 0.01444 -0.0301 0.3650 1.0000
3.500 0.7354 0.02751 0.01490 -0.0284 0.3571 1.0000
3.750 0.7522 0.02802 0.01539 -0.0267 0.3494 1.0000
4.000 0.7721 0.02849 0.01570 -0.0253 0.3434 1.0000
4.250 0.7867 0.02915 0.01644 -0.0233 0.3360 1.0000
4.500 0.8036 0.02972 0.01699 -0.0216 0.3295 1.0000
5.000 0.8368 0.03102 0.01828 -0.0181 0.3177 1.0000
5.250 0.8526 0.03169 0.01896 -0.0163 0.3119 1.0000
5.500 0.8723 0.03225 0.01940 -0.0150 0.3069 1.0000
5.750 0.8849 0.03310 0.02036 -0.0128 0.3012 1.0000
6.000 0.8979 0.03394 0.02127 -0.0107 0.2957 1.0000
6.250 0.9151 0.03462 0.02192 -0.0091 0.2910 1.0000
6.500 0.9337 0.03531 0.02254 -0.0078 0.2867 1.0000
6.750 0.9400 0.03648 0.02392 -0.0049 0.2814 1.0000
7.000 0.9520 0.03742 0.02493 -0.0028 0.2767 1.0000
7.250 0.9694 0.03815 0.02563 -0.0013 0.2727 1.0000
7.500 0.9848 0.03905 0.02652 0.0003 0.2690 1.0000
7.750 0.9844 0.04061 0.02831 0.0037 0.2646 1.0000
8.000 0.9903 0.04189 0.02971 0.0063 0.2605 1.0000
8.250 1.0033 0.04289 0.03074 0.0081 0.2570 1.0000
8.500 1.0247 0.04359 0.03136 0.0089 0.2540 1.0000
8.750 1.0157 0.04561 0.03361 0.0129 0.2506 1.0000
9.000 0.9994 0.04798 0.03620 0.0173 0.2471 1.0000
9.250 0.9862 0.05003 0.03837 0.0214 0.2439 1.0000
9.500 0.9848 0.05168 0.04006 0.0241 0.2409 1.0000
9.750 1.0042 0.05246 0.04083 0.0250 0.2382 1.0000
10.000 0.9928 0.05501 0.04347 0.0278 0.2359 1.0000
10.500 0.7432 0.08826 0.07724 0.0219 0.2226 1.0000
10.750 0.7642 0.08837 0.07735 0.0232 0.2209 1.0000
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Polar data table (+)
Polar graphs
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