BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 500,000 Max Cl/Cd: 99.52 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7b-il-500000.txt Download as CSV file: xf-vr7b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5610 0.08643 0.08443 0.0079 0.8817 0.0212
-8.250 -0.5641 0.08110 0.07911 0.0033 0.8711 0.0215
-8.000 -0.5723 0.07352 0.07146 -0.0057 0.8599 0.0216
-7.750 -0.5727 0.06774 0.06553 -0.0101 0.8496 0.0219
-7.500 -0.5689 0.06221 0.05984 -0.0135 0.8378 0.0224
-7.250 -0.5623 0.05640 0.05379 -0.0161 0.8266 0.0234
-7.000 -0.5613 0.04620 0.04269 -0.0185 0.8174 0.0252
-6.750 -0.5457 0.04260 0.03905 -0.0189 0.8058 0.0257
-6.500 -0.5266 0.04037 0.03672 -0.0192 0.7946 0.0262
-6.250 -0.5062 0.03824 0.03441 -0.0193 0.7843 0.0270
-6.000 -0.4843 0.03575 0.03168 -0.0195 0.7739 0.0284
-5.750 -0.4395 0.01729 0.01267 -0.0206 0.7486 0.0319
-5.500 -0.4172 0.01540 0.01074 -0.0208 0.7408 0.0327
-5.250 -0.3932 0.01400 0.00925 -0.0210 0.7325 0.0341
-5.000 -0.3660 0.01335 0.00828 -0.0206 0.7247 0.0378
-4.750 -0.3548 0.01998 0.01361 -0.0183 0.7308 0.0247
-4.500 -0.3269 0.01799 0.01136 -0.0183 0.7229 0.0245
-4.250 -0.2980 0.01684 0.01003 -0.0183 0.7144 0.0247
-4.000 -0.2699 0.01542 0.00842 -0.0183 0.7072 0.0255
-3.750 -0.2414 0.01436 0.00733 -0.0185 0.7001 0.0262
-3.500 -0.2129 0.01367 0.00655 -0.0185 0.6940 0.0268
-3.250 -0.1838 0.01307 0.00592 -0.0188 0.6876 0.0276
-3.000 -0.1547 0.01257 0.00536 -0.0190 0.6813 0.0286
-2.750 -0.1254 0.01215 0.00486 -0.0192 0.6754 0.0297
-2.500 -0.0957 0.01189 0.00457 -0.0195 0.6693 0.0311
-2.250 -0.0663 0.01125 0.00389 -0.0199 0.6639 0.0338
-2.000 -0.0365 0.01097 0.00357 -0.0203 0.6583 0.0364
-1.750 -0.0064 0.01067 0.00323 -0.0207 0.6522 0.0401
-1.500 0.0234 0.01042 0.00293 -0.0210 0.6466 0.0494
-1.250 0.0537 0.00916 0.00256 -0.0223 0.6409 0.2881
-1.000 0.0830 0.00808 0.00248 -0.0234 0.6350 0.5849
-0.750 0.1116 0.00776 0.00245 -0.0235 0.6295 0.6800
-0.500 0.1397 0.00751 0.00250 -0.0233 0.6233 0.7698
-0.250 0.1657 0.00735 0.00252 -0.0226 0.6174 0.8277
0.000 0.1878 0.00729 0.00259 -0.0207 0.6119 0.8878
0.250 0.2110 0.00727 0.00260 -0.0192 0.6056 0.9247
0.500 0.2328 0.00719 0.00249 -0.0175 0.5999 0.9510
0.750 0.2602 0.00709 0.00238 -0.0171 0.5937 0.9715
1.000 0.2977 0.00704 0.00229 -0.0190 0.5869 0.9939
1.250 0.3299 0.00709 0.00226 -0.0201 0.5806 1.0000
1.500 0.3605 0.00713 0.00226 -0.0208 0.5735 1.0000
1.750 0.3910 0.00721 0.00225 -0.0215 0.5672 1.0000
2.000 0.4218 0.00725 0.00228 -0.0222 0.5595 1.0000
2.500 0.4829 0.00739 0.00233 -0.0235 0.5429 1.0000
2.750 0.5132 0.00749 0.00236 -0.0242 0.5347 1.0000
3.000 0.5437 0.00757 0.00242 -0.0248 0.5266 1.0000
3.250 0.5740 0.00768 0.00249 -0.0254 0.5188 1.0000
3.500 0.6042 0.00778 0.00256 -0.0261 0.5095 1.0000
3.750 0.6345 0.00789 0.00265 -0.0267 0.5001 1.0000
4.000 0.6645 0.00803 0.00274 -0.0273 0.4913 1.0000
4.250 0.6947 0.00813 0.00286 -0.0279 0.4818 1.0000
4.500 0.7246 0.00827 0.00297 -0.0285 0.4715 1.0000
5.000 0.7844 0.00856 0.00323 -0.0297 0.4497 1.0000
5.250 0.8141 0.00872 0.00337 -0.0303 0.4393 1.0000
5.500 0.8438 0.00890 0.00353 -0.0309 0.4287 1.0000
5.750 0.8734 0.00907 0.00370 -0.0314 0.4164 1.0000
6.000 0.9028 0.00926 0.00388 -0.0320 0.4041 1.0000
6.250 0.9321 0.00947 0.00409 -0.0326 0.3921 1.0000
6.500 0.9613 0.00971 0.00432 -0.0331 0.3794 1.0000
6.750 0.9903 0.00997 0.00457 -0.0337 0.3674 1.0000
7.000 1.0191 0.01024 0.00482 -0.0343 0.3509 1.0000
7.250 1.0476 0.01058 0.00510 -0.0348 0.3260 1.0000
7.500 1.0755 0.01102 0.00544 -0.0354 0.2965 1.0000
7.750 1.1028 0.01157 0.00586 -0.0360 0.2641 1.0000
8.000 1.1292 0.01225 0.00638 -0.0366 0.2262 1.0000
8.250 1.1544 0.01309 0.00702 -0.0371 0.1897 1.0000
8.500 1.1792 0.01389 0.00769 -0.0374 0.1618 1.0000
8.750 1.2029 0.01476 0.00839 -0.0377 0.1294 1.0000
9.000 1.2257 0.01568 0.00917 -0.0379 0.1016 1.0000
9.250 1.2476 0.01661 0.00999 -0.0379 0.0826 1.0000
9.500 1.2695 0.01746 0.01080 -0.0379 0.0707 1.0000
9.750 1.2899 0.01838 0.01168 -0.0377 0.0604 1.0000
10.000 1.3092 0.01934 0.01263 -0.0374 0.0511 1.0000
10.250 1.3283 0.02023 0.01354 -0.0371 0.0436 1.0000
10.500 1.3449 0.02130 0.01464 -0.0366 0.0380 1.0000
10.750 1.3567 0.02266 0.01599 -0.0359 0.0339 1.0000
11.000 1.3664 0.02386 0.01727 -0.0346 0.0318 1.0000
11.250 1.3765 0.02516 0.01865 -0.0336 0.0299 1.0000
11.500 1.3834 0.02685 0.02038 -0.0327 0.0283 1.0000
11.750 1.3826 0.02937 0.02298 -0.0318 0.0267 1.0000
12.000 1.3929 0.03094 0.02466 -0.0314 0.0259 1.0000
12.250 1.4007 0.03280 0.02661 -0.0311 0.0249 1.0000
12.500 1.4070 0.03488 0.02877 -0.0309 0.0239 1.0000
12.750 1.4113 0.03719 0.03115 -0.0307 0.0231 1.0000
13.000 1.4117 0.03997 0.03401 -0.0306 0.0223 1.0000
13.250 1.4066 0.04334 0.03746 -0.0305 0.0217 1.0000
13.500 1.4024 0.04663 0.04085 -0.0303 0.0211 1.0000
13.750 1.4061 0.04912 0.04346 -0.0304 0.0207 1.0000
14.000 1.4081 0.05183 0.04627 -0.0305 0.0202 1.0000
14.250 1.4090 0.05470 0.04924 -0.0307 0.0196 1.0000
14.500 1.4092 0.05772 0.05235 -0.0310 0.0191 1.0000
14.750 1.4089 0.06088 0.05559 -0.0314 0.0185 1.0000
15.000 1.4076 0.06423 0.05902 -0.0320 0.0181 1.0000
15.250 1.4043 0.06785 0.06271 -0.0326 0.0177 1.0000
15.500 1.3985 0.07175 0.06668 -0.0330 0.0172 1.0000
15.750 1.3908 0.07573 0.07075 -0.0331 0.0168 1.0000
16.000 1.3903 0.07928 0.07443 -0.0341 0.0166 1.0000
16.250 1.3889 0.08301 0.07829 -0.0351 0.0163 1.0000
16.500 1.3867 0.08686 0.08226 -0.0361 0.0160 1.0000
16.750 1.3838 0.09087 0.08638 -0.0373 0.0156 1.0000
17.000 1.3802 0.09503 0.09066 -0.0386 0.0153 1.0000
17.250 1.3763 0.09934 0.09507 -0.0401 0.0150 1.0000
17.500 1.3721 0.10373 0.09956 -0.0417 0.0147 1.0000
17.750 1.3680 0.10819 0.10411 -0.0434 0.0144 1.0000
18.000 1.3637 0.11266 0.10865 -0.0452 0.0141 1.0000
18.250 1.3593 0.11711 0.11317 -0.0470 0.0138 1.0000
18.500 1.3536 0.12172 0.11785 -0.0488 0.0135 1.0000
19.000 1.3347 0.13249 0.12888 -0.0533 0.0131 1.0000
19.250 1.3264 0.13828 0.13482 -0.0564 0.0129 1.0000
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Polar data table (+)
Polar graphs
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