BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Reynolds number: 100,000 Max Cl/Cd: 39.52 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr11x-il-100000-n5.txt Download as CSV file: xf-vr11x-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-11X 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4184 0.10745 0.10264 -0.0324 1.0000 0.0528
-9.500 -0.4249 0.10503 0.10026 -0.0315 1.0000 0.0535
-9.250 -0.4300 0.10220 0.09746 -0.0314 0.9992 0.0542
-9.000 -0.4283 0.09831 0.09358 -0.0341 0.9963 0.0552
-8.750 -0.4279 0.09417 0.08946 -0.0374 0.9936 0.0562
-8.500 -0.4317 0.08996 0.08528 -0.0409 0.9903 0.0571
-8.250 -0.4396 0.08531 0.08063 -0.0458 0.9867 0.0578
-8.000 -0.4675 0.08099 0.07607 -0.0512 0.9801 0.0601
-7.750 -0.4752 0.07766 0.07245 -0.0525 0.9766 0.0604
-7.500 -0.4728 0.07309 0.06785 -0.0522 0.9743 0.0609
-7.000 -0.4610 0.06028 0.05472 -0.0498 0.9703 0.0318
-6.750 -0.4539 0.05740 0.05175 -0.0488 0.9687 0.0309
-6.500 -0.4484 0.05429 0.04846 -0.0473 0.9669 0.0298
-6.000 -0.4418 0.04630 0.03949 -0.0410 0.9612 0.0261
-5.750 -0.4290 0.04382 0.03679 -0.0395 0.9598 0.0258
-5.500 -0.4163 0.04141 0.03409 -0.0375 0.9584 0.0257
-5.250 -0.4074 0.03922 0.03152 -0.0342 0.9563 0.0259
-5.000 -0.3934 0.03708 0.02896 -0.0319 0.9540 0.0266
-4.750 -0.3759 0.03563 0.02747 -0.0308 0.9526 0.0275
-4.500 -0.3566 0.03400 0.02556 -0.0294 0.9514 0.0281
-4.250 -0.3334 0.03219 0.02338 -0.0284 0.9499 0.0281
-4.000 -0.3046 0.03044 0.02127 -0.0283 0.9483 0.0281
-3.750 -0.2844 0.02911 0.01968 -0.0266 0.9448 0.0283
-3.500 -0.2590 0.02787 0.01822 -0.0259 0.9422 0.0286
-3.250 -0.2309 0.02675 0.01693 -0.0257 0.9401 0.0292
-3.000 -0.1994 0.02574 0.01579 -0.0262 0.9379 0.0301
-2.750 -0.1655 0.02496 0.01485 -0.0272 0.9358 0.0321
-2.500 -0.1459 0.02425 0.01421 -0.0257 0.9316 0.0344
-2.250 -0.1202 0.02364 0.01360 -0.0252 0.9277 0.0368
-2.000 -0.0904 0.02307 0.01296 -0.0255 0.9246 0.0391
-1.750 -0.0588 0.02255 0.01241 -0.0262 0.9222 0.0435
-1.500 -0.0398 0.02226 0.01207 -0.0244 0.9175 0.0502
-1.250 0.1667 0.01912 0.01222 -0.0594 0.9329 1.0000
-1.000 0.2106 0.01891 0.01179 -0.0624 0.9237 1.0000
-0.750 0.2515 0.01856 0.01127 -0.0645 0.9105 1.0000
-0.500 0.2880 0.01811 0.01066 -0.0653 0.8960 1.0000
-0.250 0.3164 0.01770 0.01014 -0.0647 0.8822 1.0000
0.000 0.3414 0.01738 0.00973 -0.0634 0.8701 1.0000
0.250 0.3661 0.01708 0.00934 -0.0622 0.8593 1.0000
0.500 0.3921 0.01674 0.00892 -0.0610 0.8502 1.0000
0.750 0.4119 0.01662 0.00877 -0.0592 0.8384 1.0000
1.000 0.4315 0.01651 0.00863 -0.0573 0.8259 1.0000
1.250 0.4504 0.01642 0.00852 -0.0553 0.8115 1.0000
1.500 0.4679 0.01633 0.00844 -0.0531 0.7936 1.0000
1.750 0.4771 0.01654 0.00867 -0.0498 0.7655 1.0000
2.000 0.4852 0.01670 0.00883 -0.0461 0.7218 1.0000
2.250 0.5351 0.01488 0.00656 -0.0467 0.6388 1.0000
2.500 0.5580 0.01490 0.00590 -0.0444 0.5449 1.0000
2.750 0.5760 0.01545 0.00601 -0.0424 0.4663 1.0000
3.000 0.5941 0.01604 0.00620 -0.0407 0.4036 1.0000
3.250 0.6134 0.01659 0.00642 -0.0392 0.3559 1.0000
3.500 0.6334 0.01711 0.00667 -0.0379 0.3224 1.0000
3.750 0.6542 0.01756 0.00697 -0.0367 0.2975 1.0000
4.000 0.6751 0.01800 0.00727 -0.0356 0.2783 1.0000
4.250 0.6963 0.01843 0.00758 -0.0344 0.2637 1.0000
4.500 0.7175 0.01885 0.00792 -0.0333 0.2529 1.0000
4.750 0.7388 0.01928 0.00830 -0.0323 0.2442 1.0000
5.000 0.7602 0.01971 0.00867 -0.0312 0.2371 1.0000
5.250 0.7817 0.02015 0.00907 -0.0302 0.2303 1.0000
5.500 0.8028 0.02064 0.00948 -0.0291 0.2247 1.0000
5.750 0.8250 0.02107 0.00996 -0.0282 0.2189 1.0000
6.000 0.8468 0.02156 0.01043 -0.0273 0.2143 1.0000
6.500 0.8914 0.02261 0.01148 -0.0256 0.2059 1.0000
6.750 0.9137 0.02312 0.01205 -0.0247 0.2013 1.0000
7.000 0.9359 0.02368 0.01261 -0.0240 0.1973 1.0000
7.250 0.9588 0.02433 0.01323 -0.0233 0.1936 1.0000
7.500 0.9808 0.02486 0.01392 -0.0224 0.1891 1.0000
7.750 1.0023 0.02543 0.01455 -0.0216 0.1843 1.0000
8.000 1.0239 0.02606 0.01516 -0.0208 0.1801 1.0000
8.250 1.0450 0.02670 0.01594 -0.0199 0.1757 1.0000
8.500 1.0655 0.02731 0.01670 -0.0189 0.1711 1.0000
8.750 1.0861 0.02795 0.01741 -0.0179 0.1670 1.0000
9.000 1.1078 0.02871 0.01815 -0.0172 0.1635 1.0000
9.250 1.1273 0.02946 0.01914 -0.0161 0.1597 1.0000
9.500 1.1457 0.03017 0.02005 -0.0149 0.1552 1.0000
9.750 1.1638 0.03081 0.02076 -0.0136 0.1508 1.0000
10.000 1.1816 0.03150 0.02148 -0.0124 0.1466 1.0000
10.250 1.1953 0.03219 0.02248 -0.0105 0.1413 1.0000
10.500 1.2095 0.03276 0.02318 -0.0087 0.1365 1.0000
10.750 1.2242 0.03332 0.02372 -0.0070 0.1327 1.0000
11.000 1.2354 0.03415 0.02489 -0.0049 0.1276 1.0000
11.250 1.2465 0.03481 0.02573 -0.0027 0.1231 1.0000
11.500 1.2554 0.03535 0.02631 -0.0003 0.1197 1.0000
11.750 1.2630 0.03629 0.02751 0.0022 0.1151 1.0000
12.000 1.2702 0.03714 0.02855 0.0047 0.1108 1.0000
12.250 1.2767 0.03785 0.02934 0.0070 0.1074 1.0000
12.500 1.2829 0.03898 0.03071 0.0092 0.1028 1.0000
12.750 1.2881 0.04004 0.03195 0.0113 0.0981 1.0000
13.000 1.2921 0.04105 0.03302 0.0134 0.0947 1.0000
13.250 1.2959 0.04268 0.03492 0.0153 0.0900 1.0000
13.500 1.2978 0.04419 0.03657 0.0171 0.0859 1.0000
13.750 1.2977 0.04589 0.03835 0.0188 0.0825 1.0000
14.000 1.2961 0.04812 0.04083 0.0203 0.0781 1.0000
14.250 1.2919 0.05045 0.04328 0.0216 0.0746 1.0000
14.500 1.2850 0.05326 0.04617 0.0225 0.0717 1.0000
14.750 1.2755 0.05676 0.04994 0.0231 0.0686 1.0000
15.000 1.2628 0.06082 0.05419 0.0229 0.0662 1.0000
15.250 1.2472 0.06561 0.05912 0.0219 0.0644 1.0000
15.500 1.2289 0.07131 0.06494 0.0198 0.0630 1.0000
15.750 1.2069 0.07822 0.07199 0.0167 0.0620 1.0000
16.000 1.1774 0.08718 0.08118 0.0122 0.0614 1.0000
16.250 1.1412 0.09797 0.09214 0.0065 0.0612 1.0000
16.500 1.0977 0.11064 0.10499 -0.0002 0.0611 1.0000
16.750 1.0296 0.12918 0.12368 -0.0096 0.0609 1.0000
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Polar data table (+)
Polar graphs
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