BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 200,000 Max Cl/Cd: 34.2 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr9-il-200000.txt Download as CSV file: xf-vr9-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6403 0.08487 0.08150 0.0033 1.0000 0.0243
-8.000 -0.6445 0.08048 0.07716 -0.0002 1.0000 0.0256
-7.750 -0.6469 0.07534 0.07201 -0.0048 1.0000 0.0256
-7.500 -0.6456 0.07026 0.06686 -0.0085 1.0000 0.0264
-7.250 -0.6411 0.06490 0.06135 -0.0121 1.0000 0.0283
-6.750 -0.6280 0.05683 0.05307 -0.0142 1.0000 0.0348
-6.500 -0.6101 0.05575 0.05128 -0.0149 1.0000 0.0405
-6.250 -0.6044 0.04787 0.04338 -0.0158 1.0000 0.0421
-6.000 -0.5896 0.04466 0.04022 -0.0157 1.0000 0.0452
-5.500 -0.5558 0.03808 0.03306 -0.0153 1.0000 0.0572
-5.250 -0.5373 0.03539 0.02999 -0.0147 1.0000 0.0681
-5.000 -0.5178 0.03319 0.02748 -0.0141 1.0000 0.0808
-4.750 -0.4978 0.03075 0.02481 -0.0135 1.0000 0.0942
-4.500 -0.4757 0.02796 0.02199 -0.0129 1.0000 0.1019
-4.250 -0.4222 0.01008 0.00321 -0.0100 1.0000 0.0390
-4.000 -0.3976 0.00873 0.00143 -0.0088 1.0000 0.0412
-3.750 -0.3865 0.01756 0.00975 -0.0067 1.0000 0.0383
-3.500 -0.3612 0.01571 0.00774 -0.0055 1.0000 0.0380
-3.250 -0.3365 0.01445 0.00639 -0.0044 1.0000 0.0394
-3.000 -0.3138 0.01318 0.00508 -0.0034 1.0000 0.0442
-2.750 -0.2906 0.01230 0.00418 -0.0024 1.0000 0.0469
-2.500 -0.2668 0.01167 0.00348 -0.0015 1.0000 0.0501
-2.250 -0.2428 0.01115 0.00293 -0.0007 1.0000 0.0575
-2.000 -0.2184 0.01075 0.00249 0.0001 1.0000 0.0669
-1.750 -0.1998 0.00911 0.00199 0.0010 1.0000 0.3487
-1.500 -0.1841 0.00794 0.00186 0.0033 1.0000 0.6253
-1.250 -0.1656 0.00746 0.00181 0.0056 1.0000 0.7397
-1.000 -0.1446 0.00721 0.00178 0.0076 1.0000 0.8198
-0.750 -0.1150 0.00712 0.00178 0.0076 1.0000 0.8816
-0.500 -0.0615 0.00710 0.00174 0.0023 0.9882 0.9323
-0.250 -0.0075 0.00710 0.00173 -0.0033 0.9769 0.9693
0.000 0.0472 0.00710 0.00173 -0.0091 0.9695 1.0000
0.250 0.0917 0.00709 0.00170 -0.0127 0.9366 1.0000
0.500 0.1373 0.00711 0.00159 -0.0160 0.8623 1.0000
0.750 0.1634 0.00719 0.00156 -0.0154 0.8202 1.0000
1.000 0.1870 0.00731 0.00157 -0.0143 0.7843 1.0000
1.250 0.2104 0.00745 0.00162 -0.0132 0.7519 1.0000
1.500 0.2337 0.00762 0.00169 -0.0120 0.7170 1.0000
1.750 0.2565 0.00784 0.00183 -0.0108 0.6727 1.0000
2.000 0.2787 0.00815 0.00194 -0.0094 0.6083 1.0000
2.250 0.2976 0.00886 0.00203 -0.0075 0.4420 1.0000
2.500 0.3128 0.01094 0.00253 -0.0062 0.0767 1.0000
2.750 0.3370 0.01156 0.00304 -0.0054 0.0542 1.0000
3.000 0.3618 0.01204 0.00364 -0.0047 0.0497 1.0000
3.250 0.3860 0.01270 0.00443 -0.0039 0.0468 1.0000
3.500 0.4094 0.01358 0.00536 -0.0030 0.0451 1.0000
3.750 0.4320 0.01486 0.00664 -0.0020 0.0409 1.0000
4.000 0.4565 0.01606 0.00792 -0.0010 0.0396 1.0000
4.250 0.4817 0.01776 0.00974 0.0001 0.0393 1.0000
4.500 0.5072 0.01894 0.01108 0.0009 0.0349 1.0000
4.750 0.5334 0.02188 0.01443 0.0023 0.0382 1.0000
7.500 0.6641 0.05242 0.04895 0.0095 0.0299 1.0000
7.750 0.6576 0.05787 0.05459 0.0079 0.0292 1.0000
8.000 0.6464 0.06299 0.05980 0.0063 0.0293 1.0000
8.250 0.6320 0.06789 0.06473 0.0040 0.0297 1.0000
8.500 0.6217 0.07353 0.07037 0.0007 0.0303 1.0000
8.750 0.6148 0.07931 0.07612 -0.0023 0.0305 1.0000
9.000 0.6068 0.08551 0.08230 -0.0063 0.0303 1.0000
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Polar data table (+)
Polar graphs
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