BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.6 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr1-il-1000000-n5.txt Download as CSV file: xf-vr1-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8604 0.06219 0.05976 -0.0538 1.0000 0.0115
-13.750 -0.8955 0.05162 0.04895 -0.0627 1.0000 0.0115
-13.500 -0.9200 0.04502 0.04213 -0.0671 1.0000 0.0115
-13.250 -0.9414 0.04016 0.03706 -0.0687 1.0000 0.0115
-13.000 -0.9547 0.03693 0.03365 -0.0682 1.0000 0.0116
-12.750 -0.9658 0.03437 0.03091 -0.0663 1.0000 0.0116
-12.500 -0.9783 0.03208 0.02841 -0.0630 1.0000 0.0117
-12.250 -0.9853 0.03058 0.02678 -0.0589 1.0000 0.0117
-12.000 -0.9870 0.02912 0.02516 -0.0553 1.0000 0.0117
-11.750 -0.9837 0.02772 0.02360 -0.0523 1.0000 0.0118
-11.500 -0.9773 0.02653 0.02228 -0.0496 1.0000 0.0119
-11.250 -0.9699 0.02545 0.02107 -0.0468 1.0000 0.0119
-11.000 -0.9500 0.02349 0.01892 -0.0471 0.9965 0.0120
-10.750 -0.9284 0.02221 0.01752 -0.0471 0.9903 0.0121
-10.500 -0.9021 0.02136 0.01660 -0.0477 0.9857 0.0123
-10.250 -0.8739 0.02075 0.01594 -0.0486 0.9816 0.0124
-10.000 -0.8455 0.01999 0.01511 -0.0494 0.9768 0.0125
-9.750 -0.8151 0.01918 0.01421 -0.0507 0.9726 0.0127
-9.500 -0.7849 0.01837 0.01332 -0.0519 0.9673 0.0128
-9.250 -0.7548 0.01755 0.01240 -0.0530 0.9604 0.0129
-9.000 -0.7242 0.01687 0.01164 -0.0541 0.9533 0.0131
-8.750 -0.6968 0.01611 0.01079 -0.0545 0.9431 0.0132
-8.500 -0.6710 0.01557 0.01016 -0.0544 0.9328 0.0134
-8.250 -0.6465 0.01501 0.00951 -0.0540 0.9223 0.0136
-8.000 -0.6232 0.01450 0.00891 -0.0533 0.9112 0.0137
-7.750 -0.5998 0.01403 0.00836 -0.0525 0.9011 0.0139
-7.250 -0.5531 0.01314 0.00732 -0.0510 0.8824 0.0142
-7.000 -0.5297 0.01274 0.00684 -0.0502 0.8735 0.0143
-6.750 -0.5056 0.01237 0.00642 -0.0495 0.8649 0.0145
-6.500 -0.4815 0.01204 0.00602 -0.0488 0.8571 0.0146
-6.250 -0.4567 0.01173 0.00567 -0.0482 0.8494 0.0147
-6.000 -0.4342 0.01122 0.00510 -0.0473 0.8414 0.0150
-5.750 -0.4096 0.01088 0.00474 -0.0467 0.8342 0.0152
-5.500 -0.3847 0.01060 0.00442 -0.0461 0.8270 0.0155
-5.250 -0.3592 0.01038 0.00418 -0.0457 0.8204 0.0158
-5.000 -0.3337 0.01014 0.00391 -0.0452 0.8131 0.0161
-4.750 -0.3083 0.00992 0.00364 -0.0447 0.8066 0.0164
-4.500 -0.2824 0.00968 0.00339 -0.0443 0.8002 0.0167
-4.250 -0.2566 0.00948 0.00315 -0.0439 0.7934 0.0170
-4.000 -0.2304 0.00930 0.00294 -0.0435 0.7873 0.0173
-3.750 -0.2041 0.00912 0.00274 -0.0431 0.7807 0.0176
-3.250 -0.1518 0.00874 0.00231 -0.0423 0.7683 0.0184
-3.000 -0.1255 0.00857 0.00213 -0.0420 0.7617 0.0189
-2.750 -0.0989 0.00844 0.00198 -0.0417 0.7558 0.0195
-2.500 -0.0720 0.00831 0.00185 -0.0414 0.7495 0.0203
-2.250 -0.0452 0.00822 0.00174 -0.0411 0.7432 0.0210
-2.000 -0.0181 0.00812 0.00163 -0.0409 0.7374 0.0216
-1.750 0.0089 0.00801 0.00152 -0.0406 0.7310 0.0229
-1.500 0.0357 0.00793 0.00143 -0.0403 0.7249 0.0243
-1.250 0.0629 0.00783 0.00135 -0.0401 0.7188 0.0287
-1.000 0.0864 0.00732 0.00121 -0.0394 0.7123 0.1407
-0.750 0.1097 0.00684 0.00111 -0.0387 0.7061 0.2601
-0.500 0.1352 0.00661 0.00106 -0.0382 0.6983 0.3224
-0.250 0.1597 0.00638 0.00102 -0.0376 0.6858 0.3886
0.000 0.1842 0.00616 0.00099 -0.0369 0.6737 0.4599
0.500 0.2319 0.00576 0.00098 -0.0353 0.6437 0.6076
0.750 0.2551 0.00560 0.00100 -0.0343 0.6258 0.6790
1.000 0.2788 0.00556 0.00104 -0.0333 0.6006 0.7261
1.250 0.3023 0.00558 0.00109 -0.0323 0.5721 0.7645
1.500 0.3241 0.00581 0.00117 -0.0310 0.5143 0.7925
1.750 0.3445 0.00620 0.00131 -0.0295 0.4349 0.8128
2.000 0.3646 0.00668 0.00151 -0.0280 0.3508 0.8306
2.250 0.3840 0.00725 0.00174 -0.0265 0.2552 0.8452
2.500 0.4041 0.00778 0.00197 -0.0251 0.1724 0.8598
2.750 0.4263 0.00816 0.00216 -0.0240 0.1207 0.8735
3.000 0.4507 0.00834 0.00231 -0.0233 0.1026 0.8872
3.250 0.4756 0.00851 0.00246 -0.0227 0.0901 0.9018
3.500 0.5010 0.00867 0.00260 -0.0221 0.0805 0.9160
3.750 0.5271 0.00883 0.00276 -0.0218 0.0724 0.9302
4.000 0.5548 0.00902 0.00292 -0.0217 0.0642 0.9454
4.250 0.5854 0.00923 0.00311 -0.0224 0.0567 0.9589
4.500 0.6181 0.00946 0.00330 -0.0236 0.0502 0.9686
4.750 0.6510 0.00972 0.00351 -0.0248 0.0439 0.9741
5.000 0.6841 0.00998 0.00373 -0.0261 0.0389 0.9791
5.250 0.7150 0.01021 0.00394 -0.0269 0.0359 0.9840
5.500 0.7477 0.01049 0.00419 -0.0282 0.0328 0.9865
5.750 0.7785 0.01073 0.00442 -0.0290 0.0310 0.9893
6.000 0.8081 0.01100 0.00467 -0.0296 0.0293 0.9926
6.250 0.8372 0.01131 0.00496 -0.0301 0.0277 0.9960
6.500 0.8676 0.01157 0.00523 -0.0309 0.0269 0.9987
6.750 0.8950 0.01184 0.00550 -0.0311 0.0259 1.0000
7.000 0.9140 0.01209 0.00575 -0.0294 0.0250 1.0000
7.250 0.9333 0.01236 0.00602 -0.0278 0.0243 1.0000
7.500 0.9524 0.01268 0.00633 -0.0262 0.0236 1.0000
7.750 0.9717 0.01299 0.00667 -0.0246 0.0231 1.0000
8.000 0.9916 0.01328 0.00697 -0.0232 0.0228 1.0000
8.250 1.0114 0.01358 0.00730 -0.0217 0.0224 1.0000
8.500 1.0310 0.01390 0.00764 -0.0203 0.0220 1.0000
8.750 1.0505 0.01423 0.00799 -0.0189 0.0216 1.0000
9.000 1.0698 0.01458 0.00836 -0.0174 0.0212 1.0000
9.250 1.0887 0.01494 0.00874 -0.0159 0.0209 1.0000
9.500 1.1073 0.01533 0.00915 -0.0144 0.0205 1.0000
9.750 1.1254 0.01573 0.00957 -0.0129 0.0201 1.0000
10.000 1.1408 0.01619 0.01005 -0.0108 0.0197 1.0000
10.250 1.1540 0.01672 0.01062 -0.0084 0.0193 1.0000
10.500 1.1694 0.01714 0.01108 -0.0064 0.0192 1.0000
10.750 1.1849 0.01759 0.01157 -0.0044 0.0190 1.0000
11.000 1.2002 0.01806 0.01209 -0.0026 0.0188 1.0000
11.250 1.2154 0.01857 0.01265 -0.0008 0.0187 1.0000
11.500 1.2302 0.01911 0.01324 0.0010 0.0185 1.0000
11.750 1.2450 0.01967 0.01385 0.0027 0.0183 1.0000
12.000 1.2590 0.02029 0.01453 0.0044 0.0180 1.0000
12.250 1.2728 0.02095 0.01524 0.0061 0.0178 1.0000
12.500 1.2865 0.02162 0.01597 0.0077 0.0177 1.0000
12.750 1.2995 0.02236 0.01676 0.0093 0.0175 1.0000
13.000 1.3121 0.02314 0.01760 0.0109 0.0173 1.0000
13.250 1.3246 0.02394 0.01845 0.0123 0.0171 1.0000
13.500 1.3365 0.02481 0.01937 0.0138 0.0169 1.0000
13.750 1.3470 0.02579 0.02042 0.0153 0.0168 1.0000
14.000 1.3570 0.02685 0.02154 0.0167 0.0166 1.0000
14.250 1.3666 0.02795 0.02270 0.0180 0.0164 1.0000
14.500 1.3729 0.02937 0.02418 0.0194 0.0162 1.0000
14.750 1.3777 0.03093 0.02582 0.0208 0.0160 1.0000
15.000 1.3835 0.03248 0.02746 0.0219 0.0159 1.0000
15.250 1.3912 0.03390 0.02897 0.0229 0.0158 1.0000
15.500 1.3976 0.03547 0.03063 0.0237 0.0157 1.0000
15.750 1.4026 0.03722 0.03248 0.0245 0.0156 1.0000
16.000 1.4069 0.03909 0.03444 0.0251 0.0156 1.0000
16.250 1.4102 0.04111 0.03655 0.0256 0.0155 1.0000
16.500 1.4110 0.04345 0.03900 0.0260 0.0154 1.0000
16.750 1.4133 0.04574 0.04139 0.0262 0.0152 1.0000
17.000 1.4138 0.04828 0.04404 0.0261 0.0152 1.0000
17.250 1.4108 0.05134 0.04721 0.0259 0.0151 1.0000
17.500 1.4075 0.05458 0.05056 0.0253 0.0150 1.0000
17.750 1.4070 0.05761 0.05369 0.0246 0.0148 1.0000
18.000 1.4014 0.06141 0.05760 0.0235 0.0147 1.0000
18.250 1.3932 0.06575 0.06207 0.0221 0.0147 1.0000
18.500 1.3845 0.07038 0.06681 0.0202 0.0146 1.0000
18.750 1.3691 0.07620 0.07278 0.0176 0.0146 1.0000
19.000 1.3540 0.08229 0.07900 0.0147 0.0146 1.0000
19.250 1.3406 0.08837 0.08521 0.0115 0.0144 1.0000
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Polar data table (+)
Polar graphs
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