BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.08 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7b-il-1000000.txt Download as CSV file: xf-vr7b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5951 0.08754 0.08588 0.0157 0.8382 0.0133
-8.500 -0.5991 0.08184 0.08015 0.0110 0.8253 0.0134
-8.250 -0.6123 0.07205 0.07028 -0.0015 0.8110 0.0133
-8.000 -0.6131 0.06540 0.06347 -0.0069 0.7984 0.0135
-7.750 -0.6094 0.05966 0.05756 -0.0103 0.7861 0.0137
-7.500 -0.6018 0.05429 0.05198 -0.0127 0.7739 0.0140
-7.250 -0.5917 0.04830 0.04573 -0.0144 0.7623 0.0149
-7.000 -0.5821 0.03829 0.03493 -0.0148 0.7529 0.0159
-6.500 -0.5517 0.02770 0.02363 -0.0154 0.7300 0.0152
-6.250 -0.5323 0.02086 0.01598 -0.0150 0.7208 0.0142
-6.000 -0.5061 0.01828 0.01300 -0.0149 0.7112 0.0144
-5.750 -0.4782 0.01713 0.01163 -0.0150 0.7024 0.0151
-5.500 -0.4498 0.01624 0.01053 -0.0151 0.6942 0.0156
-5.250 -0.4211 0.01552 0.00964 -0.0152 0.6873 0.0158
-5.000 -0.3929 0.01434 0.00828 -0.0153 0.6805 0.0161
-4.750 -0.3650 0.01305 0.00690 -0.0154 0.6746 0.0165
-4.500 -0.3363 0.01243 0.00623 -0.0157 0.6687 0.0170
-4.250 -0.3073 0.01199 0.00573 -0.0159 0.6629 0.0174
-4.000 -0.2781 0.01158 0.00529 -0.0162 0.6577 0.0180
-3.750 -0.2487 0.01124 0.00491 -0.0165 0.6522 0.0188
-3.500 -0.2192 0.01094 0.00455 -0.0168 0.6471 0.0195
-3.250 -0.1897 0.01063 0.00420 -0.0171 0.6426 0.0199
-3.000 -0.1601 0.01006 0.00357 -0.0175 0.6377 0.0207
-2.750 -0.1303 0.00974 0.00320 -0.0179 0.6326 0.0216
-2.500 -0.1004 0.00952 0.00297 -0.0183 0.6277 0.0227
-2.250 -0.0705 0.00932 0.00275 -0.0186 0.6225 0.0241
-2.000 -0.0404 0.00913 0.00251 -0.0190 0.6173 0.0257
-1.750 -0.0104 0.00894 0.00230 -0.0195 0.6122 0.0287
-1.500 0.0197 0.00877 0.00213 -0.0198 0.6067 0.0329
-1.250 0.0498 0.00857 0.00196 -0.0203 0.6010 0.0474
-1.000 0.0802 0.00797 0.00179 -0.0212 0.5958 0.1823
-0.750 0.1107 0.00693 0.00164 -0.0225 0.5899 0.4524
-0.500 0.1408 0.00661 0.00162 -0.0231 0.5840 0.5616
-0.250 0.1708 0.00642 0.00160 -0.0236 0.5783 0.6206
0.000 0.2007 0.00622 0.00158 -0.0241 0.5720 0.6847
0.250 0.2298 0.00599 0.00163 -0.0243 0.5659 0.7835
0.500 0.2582 0.00586 0.00165 -0.0242 0.5593 0.8280
0.750 0.2857 0.00582 0.00169 -0.0239 0.5529 0.8705
1.000 0.3122 0.00580 0.00174 -0.0234 0.5462 0.9025
1.250 0.3402 0.00585 0.00176 -0.0233 0.5384 0.9200
1.500 0.3683 0.00587 0.00177 -0.0232 0.5304 0.9335
1.750 0.3948 0.00588 0.00175 -0.0228 0.5221 0.9476
2.000 0.4202 0.00582 0.00171 -0.0220 0.5150 0.9627
2.250 0.4487 0.00582 0.00167 -0.0221 0.5075 0.9780
2.500 0.4816 0.00582 0.00166 -0.0232 0.4992 1.0000
2.750 0.5125 0.00593 0.00171 -0.0240 0.4903 1.0000
3.000 0.5432 0.00600 0.00176 -0.0247 0.4816 1.0000
3.250 0.5739 0.00611 0.00182 -0.0254 0.4736 1.0000
3.500 0.6045 0.00621 0.00189 -0.0261 0.4647 1.0000
3.750 0.6349 0.00633 0.00197 -0.0268 0.4536 1.0000
4.000 0.6654 0.00646 0.00205 -0.0274 0.4419 1.0000
4.500 0.7259 0.00671 0.00224 -0.0288 0.4198 1.0000
4.750 0.7561 0.00686 0.00235 -0.0294 0.4094 1.0000
5.000 0.7862 0.00702 0.00248 -0.0301 0.3983 1.0000
5.250 0.8162 0.00719 0.00261 -0.0307 0.3871 1.0000
5.500 0.8461 0.00736 0.00275 -0.0314 0.3757 1.0000
5.750 0.8759 0.00754 0.00291 -0.0320 0.3650 1.0000
6.000 0.9056 0.00774 0.00308 -0.0326 0.3537 1.0000
6.250 0.9352 0.00792 0.00324 -0.0332 0.3411 1.0000
6.500 0.9646 0.00818 0.00344 -0.0339 0.3215 1.0000
6.750 0.9937 0.00857 0.00369 -0.0346 0.2916 1.0000
7.000 1.0224 0.00903 0.00400 -0.0353 0.2580 1.0000
7.250 1.0506 0.00958 0.00438 -0.0361 0.2231 1.0000
7.500 1.0784 0.01020 0.00482 -0.0368 0.1891 1.0000
7.750 1.1060 0.01074 0.00525 -0.0374 0.1658 1.0000
8.000 1.1330 0.01134 0.00570 -0.0379 0.1377 1.0000
8.250 1.1597 0.01193 0.00618 -0.0384 0.1146 1.0000
8.500 1.1854 0.01267 0.00675 -0.0389 0.0882 1.0000
8.750 1.2110 0.01330 0.00729 -0.0392 0.0730 1.0000
9.000 1.2368 0.01384 0.00780 -0.0395 0.0638 1.0000
9.250 1.2625 0.01432 0.00828 -0.0398 0.0567 1.0000
9.500 1.2874 0.01489 0.00882 -0.0399 0.0494 1.0000
9.750 1.3114 0.01552 0.00941 -0.0401 0.0404 1.0000
10.000 1.3343 0.01624 0.01007 -0.0401 0.0321 1.0000
10.250 1.3559 0.01705 0.01086 -0.0399 0.0267 1.0000
10.500 1.3786 0.01765 0.01150 -0.0399 0.0247 1.0000
10.750 1.3989 0.01846 0.01232 -0.0396 0.0224 1.0000
11.000 1.4183 0.01928 0.01319 -0.0392 0.0208 1.0000
11.250 1.4380 0.02002 0.01399 -0.0390 0.0199 1.0000
11.500 1.4550 0.02092 0.01493 -0.0386 0.0190 1.0000
11.750 1.4655 0.02202 0.01608 -0.0374 0.0181 1.0000
12.000 1.4713 0.02357 0.01771 -0.0359 0.0171 1.0000
12.250 1.4820 0.02486 0.01907 -0.0351 0.0165 1.0000
12.500 1.4940 0.02611 0.02039 -0.0346 0.0161 1.0000
12.750 1.5044 0.02755 0.02190 -0.0341 0.0156 1.0000
13.000 1.5136 0.02917 0.02359 -0.0336 0.0150 1.0000
13.250 1.5211 0.03100 0.02549 -0.0333 0.0146 1.0000
13.500 1.5258 0.03319 0.02774 -0.0330 0.0141 1.0000
13.750 1.5253 0.03599 0.03063 -0.0328 0.0136 1.0000
14.000 1.5184 0.03957 0.03432 -0.0327 0.0131 1.0000
14.250 1.5252 0.04165 0.03649 -0.0327 0.0129 1.0000
14.500 1.5303 0.04393 0.03886 -0.0328 0.0127 1.0000
14.750 1.5331 0.04650 0.04151 -0.0329 0.0124 1.0000
15.000 1.5346 0.04922 0.04431 -0.0330 0.0120 1.0000
15.250 1.5351 0.05213 0.04730 -0.0333 0.0117 1.0000
15.500 1.5343 0.05525 0.05050 -0.0337 0.0114 1.0000
15.750 1.5325 0.05858 0.05392 -0.0342 0.0112 1.0000
16.000 1.5284 0.06231 0.05773 -0.0349 0.0110 1.0000
16.250 1.5216 0.06648 0.06199 -0.0358 0.0107 1.0000
16.500 1.5116 0.07118 0.06678 -0.0368 0.0105 1.0000
16.750 1.4967 0.07671 0.07242 -0.0383 0.0103 1.0000
17.000 1.4828 0.08216 0.07799 -0.0397 0.0101 1.0000
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Polar data table (+)
Polar graphs
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