BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 200,000 Max Cl/Cd: 53.62 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr12-il-200000-n5.txt Download as CSV file: xf-vr12-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5063 0.08790 0.08451 -0.0149 1.0000 0.0144
-9.000 -0.5120 0.08175 0.07841 -0.0199 1.0000 0.0144
-8.750 -0.5232 0.07451 0.07118 -0.0273 1.0000 0.0143
-8.500 -0.5358 0.06815 0.06477 -0.0311 1.0000 0.0142
-8.250 -0.5443 0.06188 0.05837 -0.0335 1.0000 0.0143
-8.000 -0.5520 0.05616 0.05248 -0.0338 1.0000 0.0145
-7.500 -0.5496 0.04074 0.03611 -0.0349 0.9790 0.0167
-7.250 -0.5256 0.03928 0.03450 -0.0358 0.9727 0.0177
-7.000 -0.5216 0.03138 0.02547 -0.0332 0.9625 0.0202
-6.750 -0.4970 0.03065 0.02473 -0.0335 0.9567 0.0210
-6.500 -0.4751 0.02954 0.02348 -0.0329 0.9491 0.0219
-6.250 -0.4553 0.02725 0.02080 -0.0316 0.9421 0.0229
-6.000 -0.4355 0.02487 0.01783 -0.0299 0.9344 0.0245
-5.750 -0.4129 0.02360 0.01635 -0.0290 0.9286 0.0259
-5.500 -0.3894 0.02280 0.01547 -0.0283 0.9215 0.0269
-5.250 -0.3656 0.02171 0.01418 -0.0273 0.9159 0.0280
-5.000 -0.3410 0.02072 0.01295 -0.0264 0.9094 0.0295
-4.750 -0.3159 0.01993 0.01189 -0.0255 0.9035 0.0310
-4.500 -0.2916 0.01884 0.01077 -0.0248 0.8985 0.0321
-4.250 -0.2662 0.01810 0.01000 -0.0242 0.8918 0.0331
-4.000 -0.2413 0.01747 0.00930 -0.0234 0.8864 0.0345
-3.750 -0.2158 0.01694 0.00869 -0.0227 0.8809 0.0364
-3.500 -0.1901 0.01643 0.00810 -0.0221 0.8747 0.0378
-3.250 -0.1657 0.01576 0.00740 -0.0212 0.8699 0.0389
-3.000 -0.1410 0.01518 0.00685 -0.0205 0.8643 0.0407
-2.750 -0.1161 0.01477 0.00645 -0.0197 0.8576 0.0430
-2.500 -0.0921 0.01437 0.00600 -0.0186 0.8496 0.0449
-2.250 -0.0683 0.01398 0.00554 -0.0174 0.8390 0.0466
-2.000 -0.0442 0.01359 0.00510 -0.0163 0.8269 0.0487
-1.750 -0.0199 0.01323 0.00472 -0.0153 0.8154 0.0530
-1.500 0.0050 0.01296 0.00437 -0.0143 0.8046 0.0581
-1.250 0.0301 0.01265 0.00406 -0.0134 0.7930 0.0683
-1.000 0.0542 0.01217 0.00380 -0.0125 0.7811 0.1259
-0.750 0.0704 0.01086 0.00355 -0.0106 0.7699 0.4189
-0.500 0.1465 0.00977 0.00420 -0.0187 0.7575 0.9492
-0.250 0.2136 0.01020 0.00446 -0.0261 0.7422 0.9879
0.000 0.2670 0.01022 0.00434 -0.0314 0.7242 1.0000
0.250 0.2926 0.01018 0.00419 -0.0309 0.7059 1.0000
0.500 0.3180 0.01015 0.00403 -0.0303 0.6835 1.0000
0.750 0.3434 0.01016 0.00388 -0.0298 0.6536 1.0000
1.000 0.3687 0.01022 0.00373 -0.0291 0.6090 1.0000
1.250 0.3935 0.01046 0.00359 -0.0285 0.5424 1.0000
1.500 0.4183 0.01090 0.00357 -0.0281 0.4616 1.0000
1.750 0.4432 0.01135 0.00365 -0.0279 0.3951 1.0000
2.000 0.4679 0.01176 0.00376 -0.0276 0.3474 1.0000
2.250 0.4925 0.01208 0.00388 -0.0272 0.3169 1.0000
2.750 0.5412 0.01264 0.00416 -0.0263 0.2789 1.0000
3.000 0.5654 0.01289 0.00431 -0.0257 0.2650 1.0000
3.250 0.5896 0.01313 0.00447 -0.0252 0.2532 1.0000
3.500 0.6136 0.01337 0.00465 -0.0246 0.2434 1.0000
3.750 0.6374 0.01363 0.00485 -0.0239 0.2346 1.0000
4.000 0.6613 0.01386 0.00505 -0.0233 0.2268 1.0000
4.250 0.6849 0.01414 0.00526 -0.0226 0.2195 1.0000
4.500 0.7084 0.01439 0.00551 -0.0219 0.2130 1.0000
4.750 0.7318 0.01466 0.00575 -0.0212 0.2065 1.0000
5.000 0.7548 0.01497 0.00601 -0.0204 0.2006 1.0000
5.250 0.7782 0.01522 0.00629 -0.0197 0.1944 1.0000
5.500 0.8008 0.01554 0.00657 -0.0188 0.1889 1.0000
5.750 0.8236 0.01586 0.00688 -0.0180 0.1843 1.0000
6.000 0.8465 0.01615 0.00721 -0.0172 0.1796 1.0000
6.250 0.8688 0.01650 0.00755 -0.0163 0.1753 1.0000
6.500 0.8906 0.01690 0.00792 -0.0154 0.1717 1.0000
6.750 0.9132 0.01722 0.00830 -0.0145 0.1680 1.0000
7.000 0.9354 0.01757 0.00870 -0.0136 0.1642 1.0000
7.250 0.9569 0.01796 0.00909 -0.0127 0.1605 1.0000
7.500 0.9781 0.01838 0.00950 -0.0117 0.1567 1.0000
7.750 1.0002 0.01869 0.00990 -0.0108 0.1520 1.0000
8.000 1.0214 0.01905 0.01030 -0.0099 0.1476 1.0000
8.250 1.0416 0.01952 0.01074 -0.0088 0.1443 1.0000
8.500 1.0627 0.01992 0.01123 -0.0078 0.1412 1.0000
8.750 1.0837 0.02033 0.01174 -0.0068 0.1380 1.0000
9.000 1.1041 0.02076 0.01224 -0.0057 0.1350 1.0000
9.250 1.1236 0.02124 0.01274 -0.0045 0.1323 1.0000
9.500 1.1423 0.02180 0.01331 -0.0033 0.1296 1.0000
9.750 1.1623 0.02226 0.01392 -0.0022 0.1270 1.0000
10.000 1.1816 0.02274 0.01452 -0.0010 0.1240 1.0000
10.250 1.2000 0.02323 0.01509 0.0002 0.1209 1.0000
10.500 1.2166 0.02378 0.01565 0.0017 0.1175 1.0000
10.750 1.2341 0.02428 0.01629 0.0030 0.1136 1.0000
11.000 1.2511 0.02476 0.01690 0.0044 0.1093 1.0000
11.250 1.2656 0.02532 0.01750 0.0060 0.1054 1.0000
11.500 1.2791 0.02596 0.01822 0.0078 0.1020 1.0000
11.750 1.2928 0.02655 0.01897 0.0096 0.0979 1.0000
12.000 1.3039 0.02723 0.01973 0.0116 0.0940 1.0000
12.250 1.3136 0.02806 0.02060 0.0135 0.0906 1.0000
12.500 1.3269 0.02884 0.02155 0.0150 0.0862 1.0000
12.750 1.3372 0.02975 0.02255 0.0166 0.0820 1.0000
13.000 1.3461 0.03081 0.02369 0.0181 0.0784 1.0000
13.250 1.3565 0.03189 0.02491 0.0194 0.0741 1.0000
13.500 1.3636 0.03318 0.02629 0.0207 0.0704 1.0000
13.750 1.3698 0.03465 0.02785 0.0220 0.0672 1.0000
14.000 1.3756 0.03622 0.02954 0.0230 0.0639 1.0000
14.250 1.3783 0.03810 0.03150 0.0240 0.0610 1.0000
14.500 1.3778 0.04036 0.03383 0.0248 0.0586 1.0000
14.750 1.3794 0.04257 0.03622 0.0254 0.0564 1.0000
15.000 1.3781 0.04517 0.03896 0.0257 0.0544 1.0000
15.250 1.3735 0.04824 0.04215 0.0256 0.0526 1.0000
15.500 1.3654 0.05190 0.04592 0.0251 0.0510 1.0000
15.750 1.3536 0.05624 0.05037 0.0241 0.0497 1.0000
16.000 1.3433 0.06071 0.05502 0.0227 0.0486 1.0000
16.250 1.3314 0.06573 0.06024 0.0207 0.0476 1.0000
16.500 1.3159 0.07163 0.06633 0.0181 0.0466 1.0000
16.750 1.2971 0.07839 0.07327 0.0148 0.0459 1.0000
17.000 1.2751 0.08593 0.08098 0.0110 0.0452 1.0000
17.250 1.2508 0.09404 0.08924 0.0069 0.0447 1.0000
17.500 1.2255 0.10239 0.09772 0.0027 0.0442 1.0000
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Polar data table (+)
Polar graphs
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