BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 100,000 Max Cl/Cd: 46.95 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr1-il-100000.txt Download as CSV file: xf-vr1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5260 0.09168 0.08654 -0.0392 1.0000 0.1544
-9.000 -0.4804 0.08898 0.08377 -0.0325 1.0000 0.1593
-8.750 -0.4787 0.08607 0.08091 -0.0325 1.0000 0.1652
-8.500 -0.5490 0.08166 0.07669 -0.0384 1.0000 0.1699
-8.250 -0.5040 0.07850 0.07354 -0.0346 1.0000 0.1754
-8.000 -0.5128 0.07565 0.07077 -0.0338 1.0000 0.1804
-6.250 -0.6403 0.04068 0.03299 -0.0189 1.0000 0.0827
-6.000 -0.6279 0.03707 0.02939 -0.0174 1.0000 0.0802
-5.750 -0.6155 0.03436 0.02637 -0.0152 1.0000 0.0773
-5.500 -0.6015 0.03162 0.02302 -0.0128 1.0000 0.0736
-5.250 -0.5846 0.03006 0.02093 -0.0106 1.0000 0.0716
-5.000 -0.5661 0.02856 0.01918 -0.0091 1.0000 0.0716
-4.750 -0.5468 0.02702 0.01754 -0.0079 1.0000 0.0728
-4.500 -0.5273 0.02588 0.01631 -0.0067 1.0000 0.0742
-4.250 -0.5071 0.02481 0.01514 -0.0054 1.0000 0.0750
-4.000 -0.4868 0.02383 0.01409 -0.0041 1.0000 0.0758
-3.750 -0.4669 0.02298 0.01320 -0.0028 1.0000 0.0771
-3.500 -0.4476 0.02225 0.01244 -0.0014 1.0000 0.0790
-3.250 -0.4167 0.02163 0.01179 -0.0023 0.9965 0.0819
-3.000 -0.3832 0.02095 0.01124 -0.0039 0.9913 0.0890
-2.750 -0.3489 0.02046 0.01079 -0.0055 0.9858 0.1002
-2.500 -0.3177 0.01974 0.01029 -0.0064 0.9801 0.1307
-2.250 -0.3040 0.01705 0.01030 -0.0040 0.9752 0.6273
-2.000 -0.2733 0.01720 0.01115 -0.0021 0.9710 0.8338
-1.750 -0.1911 0.01836 0.01228 -0.0096 0.9721 0.9500
-1.500 -0.0501 0.01940 0.01294 -0.0298 0.9820 1.0000
-1.250 -0.0159 0.01937 0.01276 -0.0328 0.9738 1.0000
-1.000 0.0126 0.01936 0.01264 -0.0345 0.9651 1.0000
-0.750 0.0505 0.01948 0.01264 -0.0377 0.9584 1.0000
-0.500 0.0721 0.01953 0.01262 -0.0378 0.9486 1.0000
-0.250 0.1126 0.01971 0.01271 -0.0411 0.9428 1.0000
0.000 0.1286 0.01984 0.01279 -0.0400 0.9324 1.0000
0.250 0.1711 0.02004 0.01294 -0.0434 0.9269 1.0000
0.500 0.1846 0.02025 0.01311 -0.0416 0.9161 1.0000
0.750 0.2283 0.02045 0.01329 -0.0451 0.9107 1.0000
1.000 0.2408 0.02073 0.01354 -0.0429 0.8998 1.0000
1.250 0.2864 0.02089 0.01372 -0.0465 0.8944 1.0000
1.500 0.2993 0.02121 0.01404 -0.0443 0.8831 1.0000
1.750 0.3499 0.02128 0.01417 -0.0486 0.8778 1.0000
2.000 0.3632 0.02162 0.01451 -0.0463 0.8659 1.0000
2.250 0.4281 0.02112 0.01414 -0.0522 0.8559 1.0000
2.500 0.4989 0.01962 0.01278 -0.0574 0.8380 1.0000
2.750 0.5538 0.01792 0.01117 -0.0589 0.8153 1.0000
3.000 0.5909 0.01679 0.01007 -0.0580 0.7948 1.0000
3.250 0.6109 0.01635 0.00970 -0.0551 0.7737 1.0000
3.500 0.6328 0.01579 0.00917 -0.0523 0.7494 1.0000
3.750 0.6525 0.01526 0.00866 -0.0491 0.7189 1.0000
4.000 0.6699 0.01477 0.00816 -0.0454 0.6749 1.0000
4.250 0.6803 0.01449 0.00760 -0.0402 0.5774 1.0000
4.500 0.6653 0.01632 0.00760 -0.0315 0.2824 1.0000
4.750 0.6634 0.01817 0.00860 -0.0266 0.1918 1.0000
5.000 0.6729 0.01931 0.00947 -0.0233 0.1628 1.0000
5.250 0.6854 0.02040 0.01034 -0.0206 0.1445 1.0000
5.500 0.7023 0.02149 0.01131 -0.0186 0.1311 1.0000
5.750 0.7232 0.02269 0.01242 -0.0173 0.1207 1.0000
6.000 0.7480 0.02422 0.01372 -0.0169 0.1119 1.0000
6.250 0.7732 0.02536 0.01499 -0.0161 0.1061 1.0000
6.500 0.7989 0.02675 0.01632 -0.0157 0.1005 1.0000
6.750 0.8253 0.02852 0.01816 -0.0154 0.0959 1.0000
7.000 0.8497 0.03007 0.01993 -0.0146 0.0932 1.0000
7.250 0.8733 0.03183 0.02190 -0.0137 0.0910 1.0000
7.500 0.8956 0.03359 0.02380 -0.0128 0.0886 1.0000
7.750 0.9174 0.03570 0.02596 -0.0122 0.0860 1.0000
8.000 0.9364 0.03897 0.02941 -0.0113 0.0846 1.0000
8.250 0.9518 0.04144 0.03224 -0.0094 0.0843 1.0000
8.500 0.9667 0.04458 0.03567 -0.0078 0.0845 1.0000
8.750 0.9805 0.04710 0.03853 -0.0058 0.0852 1.0000
9.000 0.9756 0.04968 0.04195 -0.0009 0.0880 1.0000
9.250 0.9664 0.05446 0.04734 0.0030 0.0921 1.0000
9.500 0.9635 0.05862 0.05179 0.0056 0.0946 1.0000
9.750 0.8530 0.05618 0.05038 0.0155 0.1081 1.0000
10.000 0.7267 0.09502 0.08959 -0.0023 0.2066 1.0000
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Polar data table (+)
Polar graphs
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