BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL WITH TAB (vr8b-il) Reynolds number: 100,000 Max Cl/Cd: 41.56 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr8b-il-100000.txt Download as CSV file: xf-vr8b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 AIRFOIL WITH TAB
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5375 0.10388 0.09970 0.0172 1.0000 0.0944
-8.750 -0.5551 0.09972 0.09560 0.0118 1.0000 0.0958
-8.500 -0.6577 0.10486 0.10056 0.0286 1.0000 0.0871
-8.250 -0.6547 0.10072 0.09642 0.0264 1.0000 0.0907
-8.000 -0.6588 0.09596 0.09172 0.0201 1.0000 0.0941
-7.750 -0.6707 0.08965 0.08532 0.0038 1.0000 0.0960
-7.500 -0.6593 0.08407 0.07982 0.0063 1.0000 0.0987
-7.250 -0.6471 0.08052 0.07629 0.0076 1.0000 0.1034
-7.000 -0.6522 0.07507 0.07029 -0.0065 1.0000 0.1109
-6.750 -0.6326 0.06983 0.06543 -0.0019 1.0000 0.1149
-6.500 -0.6238 0.06486 0.06011 -0.0081 1.0000 0.1261
-6.250 -0.6061 0.06114 0.05652 -0.0067 1.0000 0.1337
-6.000 -0.5908 0.05693 0.05220 -0.0086 1.0000 0.1467
-5.750 -0.5751 0.05299 0.04797 -0.0115 1.0000 0.1694
-5.500 -0.5566 0.04960 0.04468 -0.0109 1.0000 0.1877
-4.500 -0.4201 0.02900 0.02093 -0.0179 1.0000 0.0779
-4.250 -0.3861 0.02689 0.01797 -0.0173 1.0000 0.0682
-4.000 -0.3566 0.02400 0.01480 -0.0176 1.0000 0.0692
-3.750 -0.3268 0.02182 0.01243 -0.0177 1.0000 0.0698
-3.500 -0.2969 0.02010 0.01058 -0.0176 1.0000 0.0696
-3.250 -0.2681 0.01846 0.00893 -0.0176 1.0000 0.0709
-3.000 -0.2400 0.01726 0.00783 -0.0177 1.0000 0.0759
-2.750 -0.2118 0.01633 0.00690 -0.0178 1.0000 0.0811
-2.500 -0.1839 0.01531 0.00591 -0.0181 1.0000 0.0861
-2.250 -0.1556 0.01456 0.00516 -0.0185 1.0000 0.0980
-2.000 -0.1371 0.01152 0.00463 -0.0178 1.0000 0.6219
-1.750 -0.1344 0.01103 0.00498 -0.0104 1.0000 0.8458
-1.500 -0.0880 0.01102 0.00492 -0.0120 1.0000 0.9862
-1.250 -0.0678 0.01114 0.00486 -0.0129 1.0000 1.0000
-1.000 -0.0258 0.01131 0.00477 -0.0173 0.9908 1.0000
-0.750 0.0305 0.01144 0.00469 -0.0238 0.9779 1.0000
-0.500 0.0823 0.01161 0.00471 -0.0290 0.9589 1.0000
-0.250 0.1105 0.01170 0.00467 -0.0284 0.9217 1.0000
0.000 0.1295 0.01174 0.00456 -0.0258 0.8935 1.0000
0.250 0.1510 0.01184 0.00455 -0.0242 0.8747 1.0000
0.500 0.1736 0.01195 0.00457 -0.0228 0.8570 1.0000
0.750 0.1965 0.01207 0.00460 -0.0216 0.8411 1.0000
1.000 0.2170 0.01214 0.00456 -0.0194 0.8216 1.0000
1.250 0.2376 0.01218 0.00447 -0.0172 0.7986 1.0000
1.500 0.2598 0.01224 0.00442 -0.0154 0.7779 1.0000
1.750 0.2834 0.01231 0.00439 -0.0139 0.7556 1.0000
2.000 0.3089 0.01244 0.00444 -0.0131 0.7376 1.0000
2.250 0.3358 0.01260 0.00461 -0.0128 0.7232 1.0000
2.500 0.3628 0.01275 0.00476 -0.0124 0.7081 1.0000
2.750 0.3896 0.01290 0.00490 -0.0120 0.6919 1.0000
3.000 0.4167 0.01306 0.00507 -0.0116 0.6759 1.0000
3.250 0.4441 0.01320 0.00530 -0.0113 0.6572 1.0000
3.500 0.4706 0.01328 0.00540 -0.0107 0.6326 1.0000
3.750 0.4982 0.01339 0.00558 -0.0103 0.6074 1.0000
4.000 0.5251 0.01347 0.00568 -0.0097 0.5743 1.0000
4.250 0.5525 0.01354 0.00580 -0.0093 0.5206 1.0000
4.500 0.5789 0.01393 0.00583 -0.0089 0.3905 1.0000
4.750 0.6019 0.01700 0.00710 -0.0100 0.0992 1.0000
5.000 0.6290 0.01820 0.00825 -0.0103 0.0824 1.0000
5.250 0.6554 0.01938 0.00949 -0.0104 0.0770 1.0000
5.500 0.6813 0.02054 0.01079 -0.0101 0.0739 1.0000
5.750 0.7067 0.02181 0.01205 -0.0098 0.0697 1.0000
6.000 0.7310 0.02380 0.01391 -0.0093 0.0661 1.0000
6.250 0.7580 0.02556 0.01578 -0.0088 0.0651 1.0000
6.500 0.7855 0.02755 0.01801 -0.0082 0.0639 1.0000
6.750 0.8125 0.02951 0.02033 -0.0079 0.0605 1.0000
7.000 0.8390 0.03254 0.02381 -0.0073 0.0607 1.0000
7.250 0.8637 0.03602 0.02781 -0.0068 0.0609 1.0000
7.500 0.8858 0.03950 0.03182 -0.0064 0.0595 1.0000
7.750 0.9044 0.04475 0.03764 -0.0061 0.0631 1.0000
8.000 0.9181 0.05221 0.04599 -0.0056 0.0762 1.0000
10.000 0.8193 0.11694 0.11240 -0.0464 0.1389 1.0000
10.250 0.6639 0.11377 0.10938 -0.0322 0.1528 1.0000
10.500 0.6819 0.11779 0.11342 -0.0299 0.1468 1.0000
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Polar data table (+)
Polar graphs
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