BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.81 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr1-il-1000000.txt Download as CSV file: xf-vr1-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5278 0.06247 0.06059 -0.0534 1.0000 0.0210
-11.250 -0.5586 0.05348 0.05150 -0.0593 1.0000 0.0210
-11.000 -0.5849 0.04707 0.04499 -0.0629 1.0000 0.0209
-10.750 -0.6185 0.04215 0.03993 -0.0648 1.0000 0.0209
-10.500 -0.6434 0.03884 0.03651 -0.0639 1.0000 0.0209
-10.250 -0.6696 0.03671 0.03426 -0.0601 1.0000 0.0210
-10.000 -0.6909 0.03460 0.03204 -0.0552 1.0000 0.0210
-9.750 -0.7095 0.03255 0.02985 -0.0501 1.0000 0.0210
-9.500 -0.7043 0.02865 0.02566 -0.0508 0.9957 0.0210
-9.250 -0.7124 0.01973 0.01633 -0.0511 0.9891 0.0216
-9.000 -0.6883 0.01764 0.01419 -0.0523 0.9861 0.0218
-8.750 -0.6638 0.01570 0.01216 -0.0534 0.9831 0.0221
-8.500 -0.6413 0.01402 0.01036 -0.0539 0.9770 0.0225
-8.250 -0.6606 0.02298 0.01853 -0.0505 0.9769 0.0202
-8.000 -0.6327 0.02055 0.01583 -0.0515 0.9734 0.0198
-7.750 -0.6056 0.01844 0.01348 -0.0519 0.9680 0.0193
-7.500 -0.5763 0.01710 0.01199 -0.0525 0.9619 0.0193
-7.250 -0.5463 0.01595 0.01071 -0.0532 0.9559 0.0193
-7.000 -0.5197 0.01507 0.00973 -0.0532 0.9470 0.0194
-6.750 -0.4933 0.01428 0.00885 -0.0530 0.9385 0.0195
-6.500 -0.4681 0.01363 0.00812 -0.0525 0.9290 0.0196
-6.250 -0.4438 0.01303 0.00746 -0.0518 0.9197 0.0198
-6.000 -0.4194 0.01248 0.00683 -0.0511 0.9107 0.0200
-5.750 -0.3953 0.01201 0.00632 -0.0503 0.9017 0.0203
-5.250 -0.3453 0.01141 0.00560 -0.0491 0.8849 0.0209
-4.750 -0.2995 0.01026 0.00436 -0.0472 0.8687 0.0216
-4.500 -0.2759 0.00984 0.00389 -0.0463 0.8610 0.0220
-4.250 -0.2511 0.00952 0.00355 -0.0457 0.8536 0.0224
-4.000 -0.2258 0.00926 0.00326 -0.0451 0.8463 0.0229
-3.750 -0.2002 0.00903 0.00299 -0.0446 0.8394 0.0234
-3.500 -0.1744 0.00881 0.00275 -0.0441 0.8322 0.0239
-3.250 -0.1483 0.00863 0.00252 -0.0437 0.8256 0.0245
-3.000 -0.1219 0.00847 0.00235 -0.0433 0.8187 0.0252
-2.750 -0.0961 0.00825 0.00209 -0.0428 0.8120 0.0266
-2.500 -0.0695 0.00809 0.00192 -0.0424 0.8055 0.0281
-2.250 -0.0428 0.00797 0.00178 -0.0421 0.7987 0.0297
-2.000 -0.0163 0.00783 0.00165 -0.0417 0.7925 0.0358
-1.750 0.0056 0.00715 0.00145 -0.0408 0.7856 0.1668
-1.500 0.0268 0.00648 0.00129 -0.0397 0.7790 0.3226
-1.250 0.0486 0.00591 0.00121 -0.0387 0.7726 0.4619
-1.000 0.0713 0.00551 0.00115 -0.0377 0.7659 0.5645
-0.750 0.0955 0.00530 0.00114 -0.0369 0.7596 0.6362
-0.500 0.1203 0.00512 0.00114 -0.0361 0.7526 0.6917
-0.250 0.1455 0.00504 0.00114 -0.0354 0.7445 0.7302
0.000 0.1706 0.00494 0.00115 -0.0346 0.7340 0.7677
0.250 0.1958 0.00489 0.00117 -0.0338 0.7242 0.8022
0.500 0.2216 0.00487 0.00119 -0.0332 0.7145 0.8275
0.750 0.2469 0.00484 0.00123 -0.0324 0.7021 0.8536
1.000 0.2728 0.00486 0.00126 -0.0317 0.6892 0.8721
1.250 0.2986 0.00489 0.00129 -0.0311 0.6735 0.8872
1.500 0.3244 0.00495 0.00133 -0.0304 0.6562 0.9015
1.750 0.3500 0.00503 0.00137 -0.0298 0.6370 0.9143
2.000 0.3754 0.00513 0.00143 -0.0291 0.6163 0.9258
2.250 0.4014 0.00526 0.00149 -0.0285 0.5868 0.9351
2.500 0.4256 0.00547 0.00156 -0.0277 0.5463 0.9450
2.750 0.4492 0.00587 0.00171 -0.0268 0.4778 0.9549
3.000 0.4714 0.00664 0.00199 -0.0260 0.3573 0.9635
3.250 0.4929 0.00751 0.00232 -0.0252 0.2347 0.9725
3.500 0.5229 0.00826 0.00266 -0.0262 0.1401 0.9765
3.750 0.5554 0.00868 0.00290 -0.0274 0.1054 0.9803
4.000 0.5880 0.00897 0.00312 -0.0286 0.0897 0.9846
4.250 0.6262 0.00926 0.00333 -0.0310 0.0768 0.9871
4.500 0.6628 0.00955 0.00355 -0.0330 0.0652 0.9902
4.750 0.6969 0.00985 0.00377 -0.0346 0.0554 0.9935
5.000 0.7310 0.01013 0.00401 -0.0361 0.0481 0.9956
5.250 0.7647 0.01044 0.00427 -0.0376 0.0426 0.9977
5.500 0.7979 0.01073 0.00453 -0.0390 0.0392 0.9995
5.750 0.8195 0.01105 0.00484 -0.0379 0.0367 1.0000
6.000 0.8369 0.01125 0.00506 -0.0359 0.0354 1.0000
6.250 0.8543 0.01149 0.00530 -0.0339 0.0341 1.0000
6.500 0.8713 0.01179 0.00560 -0.0318 0.0327 1.0000
6.750 0.8869 0.01223 0.00605 -0.0295 0.0312 1.0000
7.000 0.9062 0.01248 0.00631 -0.0279 0.0306 1.0000
7.250 0.9253 0.01277 0.00662 -0.0262 0.0299 1.0000
7.500 0.9446 0.01308 0.00695 -0.0246 0.0291 1.0000
7.750 0.9636 0.01341 0.00730 -0.0230 0.0283 1.0000
8.000 0.9820 0.01380 0.00769 -0.0214 0.0277 1.0000
8.250 0.9982 0.01435 0.00825 -0.0193 0.0269 1.0000
8.500 1.0126 0.01503 0.00899 -0.0170 0.0263 1.0000
8.750 1.0317 0.01540 0.00939 -0.0155 0.0260 1.0000
9.000 1.0506 0.01578 0.00980 -0.0140 0.0256 1.0000
9.250 1.0689 0.01620 0.01027 -0.0124 0.0251 1.0000
9.500 1.0868 0.01663 0.01072 -0.0108 0.0246 1.0000
9.750 1.1021 0.01711 0.01124 -0.0087 0.0242 1.0000
10.000 1.1169 0.01758 0.01174 -0.0066 0.0239 1.0000
10.250 1.1316 0.01807 0.01226 -0.0045 0.0235 1.0000
10.500 1.1455 0.01866 0.01288 -0.0024 0.0232 1.0000
10.750 1.1587 0.01934 0.01359 -0.0003 0.0228 1.0000
11.000 1.1695 0.02030 0.01460 0.0020 0.0224 1.0000
11.250 1.1784 0.02167 0.01606 0.0045 0.0220 1.0000
11.500 1.1931 0.02229 0.01674 0.0061 0.0219 1.0000
11.750 1.2075 0.02293 0.01745 0.0077 0.0217 1.0000
12.000 1.2204 0.02378 0.01839 0.0095 0.0215 1.0000
12.250 1.2333 0.02459 0.01926 0.0111 0.0212 1.0000
12.500 1.2458 0.02542 0.02016 0.0127 0.0210 1.0000
12.750 1.2573 0.02634 0.02116 0.0143 0.0207 1.0000
13.000 1.2682 0.02731 0.02221 0.0158 0.0204 1.0000
13.250 1.2787 0.02830 0.02327 0.0173 0.0201 1.0000
13.500 1.2877 0.02949 0.02455 0.0188 0.0200 1.0000
13.750 1.2963 0.03070 0.02583 0.0202 0.0198 1.0000
14.000 1.3041 0.03199 0.02720 0.0215 0.0196 1.0000
14.250 1.3111 0.03337 0.02865 0.0228 0.0194 1.0000
14.500 1.3166 0.03495 0.03031 0.0239 0.0192 1.0000
14.750 1.3219 0.03654 0.03196 0.0250 0.0190 1.0000
15.000 1.3246 0.03848 0.03399 0.0260 0.0189 1.0000
15.250 1.3251 0.04071 0.03632 0.0269 0.0188 1.0000
15.500 1.3169 0.04398 0.03973 0.0278 0.0185 1.0000
15.750 1.3061 0.04766 0.04360 0.0284 0.0184 1.0000
16.000 1.2971 0.05116 0.04727 0.0285 0.0182 1.0000
16.250 1.2964 0.05381 0.05003 0.0281 0.0181 1.0000
16.500 1.2869 0.05774 0.05412 0.0275 0.0181 1.0000
16.750 1.2764 0.06204 0.05856 0.0263 0.0181 1.0000
17.000 1.2645 0.06681 0.06348 0.0247 0.0180 1.0000
17.250 1.2602 0.07078 0.06756 0.0228 0.0178 1.0000
17.500 1.2389 0.07760 0.07456 0.0196 0.0178 1.0000
17.750 1.2200 0.08454 0.08166 0.0159 0.0178 1.0000
18.000 1.1990 0.09234 0.08963 0.0113 0.0178 1.0000
18.250 1.1609 0.10407 0.10157 0.0042 0.0178 1.0000
18.500 1.1148 0.11860 0.11632 -0.0049 0.0179 1.0000
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Polar data table (+)
Polar graphs
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