BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 50,000 Max Cl/Cd: 30.75 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7b-il-50000.txt Download as CSV file: xf-vr7b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4261 0.10266 0.09687 0.0077 1.0000 0.3091
-8.000 -0.4172 0.09932 0.09356 0.0072 1.0000 0.3267
-7.750 -0.4157 0.09667 0.09098 0.0063 1.0000 0.3471
-7.500 -0.4025 0.09299 0.08735 0.0065 1.0000 0.3682
-7.250 -0.4021 0.09099 0.08543 0.0064 1.0000 0.3956
-7.000 -0.3799 0.08733 0.08179 0.0077 1.0000 0.4258
-6.750 -0.3566 0.08355 0.07803 0.0084 1.0000 0.4540
-6.500 -0.3405 0.08028 0.07480 0.0087 1.0000 0.4811
-6.250 -0.3291 0.07747 0.07204 0.0091 1.0000 0.5096
-6.000 -0.3229 0.07522 0.06986 0.0101 1.0000 0.5390
-5.000 -0.4612 0.05109 0.04413 -0.0309 1.0000 0.1758
-4.750 -0.4421 0.04707 0.03971 -0.0314 1.0000 0.1587
-4.500 -0.4199 0.04372 0.03561 -0.0320 1.0000 0.1441
-4.250 -0.3997 0.04081 0.03254 -0.0321 1.0000 0.1385
-4.000 -0.3732 0.03868 0.02940 -0.0323 1.0000 0.1296
-3.750 -0.3496 0.03649 0.02700 -0.0325 1.0000 0.1278
-3.500 -0.3079 0.03456 0.02457 -0.0354 0.9946 0.1287
-3.250 -0.2624 0.03266 0.02236 -0.0389 0.9867 0.1320
-3.000 -0.2170 0.03124 0.02078 -0.0421 0.9784 0.1357
-2.750 -0.1687 0.03029 0.01962 -0.0454 0.9699 0.1456
-2.500 -0.1268 0.02944 0.01878 -0.0478 0.9606 0.1613
-2.250 -0.0855 0.02859 0.01809 -0.0506 0.9509 0.1929
-2.000 -0.0164 0.02539 0.01810 -0.0496 0.9475 1.0000
-1.750 0.0171 0.02591 0.01809 -0.0521 0.9354 1.0000
-1.500 0.0473 0.02648 0.01828 -0.0541 0.9235 1.0000
-1.250 0.0730 0.02708 0.01856 -0.0552 0.9116 1.0000
-1.000 0.0966 0.02771 0.01890 -0.0558 0.9002 1.0000
-0.750 0.1249 0.02839 0.01931 -0.0571 0.8892 1.0000
-0.500 0.1658 0.02910 0.01976 -0.0603 0.8794 1.0000
-0.250 0.1848 0.02979 0.02027 -0.0600 0.8678 1.0000
0.000 0.2076 0.03055 0.02085 -0.0603 0.8570 1.0000
0.250 0.2429 0.03132 0.02144 -0.0623 0.8472 1.0000
0.500 0.2676 0.03210 0.02208 -0.0628 0.8362 1.0000
0.750 0.2871 0.03298 0.02285 -0.0625 0.8254 1.0000
1.000 0.3193 0.03381 0.02356 -0.0639 0.8157 1.0000
1.250 0.3432 0.03469 0.02435 -0.0642 0.8049 1.0000
1.500 0.3607 0.03574 0.02532 -0.0638 0.7944 1.0000
1.750 0.3936 0.03658 0.02610 -0.0650 0.7850 1.0000
2.000 0.4113 0.03769 0.02716 -0.0647 0.7745 1.0000
2.250 0.4290 0.03888 0.02831 -0.0644 0.7644 1.0000
2.500 0.4655 0.03968 0.02908 -0.0658 0.7557 1.0000
2.750 0.4717 0.04121 0.03058 -0.0646 0.7450 1.0000
3.000 0.4940 0.04242 0.03179 -0.0647 0.7356 1.0000
3.250 0.5200 0.04355 0.03292 -0.0652 0.7263 1.0000
3.500 0.5280 0.04521 0.03458 -0.0642 0.7164 1.0000
3.750 0.5604 0.04624 0.03564 -0.0651 0.7074 1.0000
4.000 0.5677 0.04803 0.03745 -0.0642 0.6975 1.0000
4.250 0.5835 0.04965 0.03911 -0.0640 0.6881 1.0000
4.500 0.6145 0.05076 0.04028 -0.0647 0.6786 1.0000
4.750 0.6151 0.05298 0.04252 -0.0635 0.6682 1.0000
5.000 0.6366 0.05440 0.04400 -0.0634 0.6570 1.0000
5.250 0.6685 0.05523 0.04493 -0.0635 0.6442 1.0000
5.500 0.6893 0.05648 0.04626 -0.0630 0.6311 1.0000
5.750 0.6945 0.05857 0.04841 -0.0621 0.6182 1.0000
6.000 0.7062 0.06050 0.05041 -0.0616 0.6060 1.0000
6.250 0.7263 0.06200 0.05203 -0.0612 0.5936 1.0000
6.500 0.7546 0.06300 0.05316 -0.0609 0.5811 1.0000
6.750 0.7852 0.06361 0.05393 -0.0603 0.5675 1.0000
7.000 0.7996 0.06516 0.05558 -0.0593 0.5526 1.0000
7.250 0.8207 0.06614 0.05672 -0.0583 0.5372 1.0000
7.500 0.8401 0.06723 0.05795 -0.0572 0.5218 1.0000
7.750 0.8586 0.06839 0.05926 -0.0560 0.5065 1.0000
8.000 0.8779 0.06945 0.06047 -0.0548 0.4911 1.0000
8.250 0.8874 0.07136 0.06252 -0.0537 0.4748 1.0000
8.500 0.8896 0.07400 0.06526 -0.0529 0.4579 1.0000
8.750 0.8960 0.07599 0.06736 -0.0517 0.4394 1.0000
9.000 1.0944 0.04970 0.04191 -0.0375 0.4127 1.0000
9.250 1.1587 0.04302 0.03530 -0.0331 0.3823 1.0000
9.500 1.1880 0.04095 0.03321 -0.0300 0.3455 1.0000
9.750 1.2105 0.03987 0.03189 -0.0270 0.3045 1.0000
10.000 1.2278 0.03993 0.03148 -0.0245 0.2651 1.0000
10.250 1.2354 0.04164 0.03299 -0.0224 0.2346 1.0000
10.500 1.2434 0.04364 0.03484 -0.0205 0.2094 1.0000
10.750 1.2525 0.04611 0.03727 -0.0190 0.1888 1.0000
11.000 1.2618 0.04878 0.03994 -0.0175 0.1716 1.0000
11.250 1.2717 0.05167 0.04288 -0.0163 0.1578 1.0000
11.500 1.2832 0.05471 0.04599 -0.0152 0.1467 1.0000
11.750 1.3034 0.05777 0.04896 -0.0146 0.1361 1.0000
12.000 1.2875 0.06150 0.05318 -0.0126 0.1333 1.0000
12.250 1.2725 0.06544 0.05746 -0.0112 0.1304 1.0000
12.500 1.3001 0.06897 0.06087 -0.0109 0.1227 1.0000
12.750 1.2770 0.07348 0.06573 -0.0099 0.1223 1.0000
13.000 1.2516 0.07868 0.07121 -0.0098 0.1222 1.0000
13.250 1.2243 0.08463 0.07741 -0.0109 0.1224 1.0000
13.500 1.1959 0.09142 0.08440 -0.0128 0.1229 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)