BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 500,000 Max Cl/Cd: 61.12 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr1-il-500000-n5.txt Download as CSV file: xf-vr1-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7024 0.06845 0.06553 -0.0507 1.0000 0.0145
-12.250 -0.7283 0.05899 0.05592 -0.0589 1.0000 0.0144
-12.000 -0.7494 0.05268 0.04945 -0.0637 1.0000 0.0144
-11.750 -0.7751 0.04741 0.04398 -0.0659 1.0000 0.0144
-11.500 -0.7998 0.04349 0.03983 -0.0651 1.0000 0.0144
-11.250 -0.8196 0.04080 0.03695 -0.0618 1.0000 0.0144
-11.000 -0.8368 0.03867 0.03463 -0.0571 1.0000 0.0145
-10.750 -0.8441 0.03647 0.03224 -0.0536 1.0000 0.0145
-10.500 -0.8505 0.03427 0.02976 -0.0497 1.0000 0.0146
-10.250 -0.8526 0.03253 0.02776 -0.0459 1.0000 0.0147
-10.000 -0.8401 0.03020 0.02521 -0.0452 0.9972 0.0148
-9.750 -0.8175 0.02850 0.02339 -0.0459 0.9917 0.0150
-9.500 -0.7933 0.02702 0.02177 -0.0466 0.9865 0.0152
-9.250 -0.7677 0.02570 0.02031 -0.0473 0.9820 0.0153
-9.000 -0.7423 0.02447 0.01895 -0.0478 0.9764 0.0155
-8.750 -0.7143 0.02302 0.01731 -0.0488 0.9724 0.0157
-8.500 -0.6866 0.02185 0.01600 -0.0495 0.9673 0.0159
-8.250 -0.6585 0.02070 0.01470 -0.0502 0.9614 0.0161
-8.000 -0.6283 0.01963 0.01347 -0.0512 0.9566 0.0164
-7.750 -0.6004 0.01870 0.01242 -0.0517 0.9496 0.0166
-7.500 -0.5713 0.01781 0.01141 -0.0523 0.9428 0.0168
-7.250 -0.5438 0.01703 0.01052 -0.0525 0.9352 0.0170
-7.000 -0.5167 0.01633 0.00972 -0.0526 0.9270 0.0172
-6.750 -0.4910 0.01572 0.00902 -0.0523 0.9184 0.0175
-6.500 -0.4652 0.01519 0.00840 -0.0520 0.9098 0.0176
-6.250 -0.4402 0.01476 0.00789 -0.0515 0.9013 0.0178
-6.000 -0.4173 0.01397 0.00708 -0.0507 0.8926 0.0183
-5.750 -0.3936 0.01349 0.00658 -0.0500 0.8842 0.0187
-5.500 -0.3694 0.01305 0.00610 -0.0494 0.8762 0.0191
-5.250 -0.3453 0.01264 0.00566 -0.0487 0.8686 0.0194
-5.000 -0.3209 0.01227 0.00524 -0.0480 0.8607 0.0196
-4.750 -0.2964 0.01191 0.00485 -0.0473 0.8534 0.0201
-4.500 -0.2717 0.01159 0.00448 -0.0467 0.8459 0.0204
-4.250 -0.2466 0.01131 0.00416 -0.0461 0.8392 0.0208
-4.000 -0.2213 0.01105 0.00386 -0.0456 0.8318 0.0212
-3.750 -0.1960 0.01078 0.00355 -0.0450 0.8251 0.0216
-3.500 -0.1709 0.01048 0.00323 -0.0445 0.8185 0.0222
-3.250 -0.1452 0.01026 0.00299 -0.0440 0.8116 0.0232
-3.000 -0.1191 0.01008 0.00278 -0.0436 0.8054 0.0243
-2.750 -0.0928 0.00992 0.00260 -0.0432 0.7987 0.0251
-2.500 -0.0665 0.00977 0.00241 -0.0428 0.7923 0.0262
-2.250 -0.0401 0.00962 0.00225 -0.0424 0.7860 0.0280
-2.000 -0.0137 0.00948 0.00212 -0.0421 0.7795 0.0315
-1.750 0.0090 0.00890 0.00192 -0.0412 0.7735 0.1322
-1.500 0.0308 0.00823 0.00177 -0.0403 0.7667 0.2705
-1.250 0.0553 0.00792 0.00167 -0.0397 0.7604 0.3392
-1.000 0.0792 0.00757 0.00161 -0.0390 0.7543 0.4245
-0.750 0.1030 0.00725 0.00156 -0.0383 0.7478 0.5051
-0.500 0.1260 0.00695 0.00154 -0.0372 0.7417 0.5879
-0.250 0.1494 0.00671 0.00156 -0.0362 0.7352 0.6629
0.000 0.1734 0.00655 0.00160 -0.0352 0.7286 0.7191
0.250 0.1976 0.00644 0.00164 -0.0342 0.7197 0.7681
0.500 0.2223 0.00641 0.00167 -0.0332 0.7079 0.8045
0.750 0.2478 0.00639 0.00172 -0.0325 0.6956 0.8302
1.000 0.2738 0.00641 0.00175 -0.0318 0.6819 0.8482
1.250 0.2999 0.00645 0.00177 -0.0312 0.6661 0.8617
1.500 0.3253 0.00653 0.00180 -0.0305 0.6454 0.8759
1.750 0.3506 0.00663 0.00185 -0.0298 0.6193 0.8899
2.000 0.3752 0.00680 0.00190 -0.0289 0.5808 0.9023
2.250 0.3987 0.00707 0.00198 -0.0279 0.5277 0.9142
2.500 0.4204 0.00750 0.00212 -0.0267 0.4565 0.9261
2.750 0.4407 0.00826 0.00241 -0.0254 0.3450 0.9379
3.000 0.4630 0.00916 0.00279 -0.0249 0.2228 0.9486
3.250 0.4896 0.00986 0.00312 -0.0250 0.1405 0.9593
3.500 0.5214 0.01028 0.00338 -0.0261 0.1084 0.9688
3.750 0.5565 0.01061 0.00363 -0.0279 0.0923 0.9750
4.000 0.5897 0.01089 0.00385 -0.0292 0.0807 0.9800
4.250 0.6206 0.01117 0.00407 -0.0300 0.0710 0.9845
4.500 0.6537 0.01146 0.00431 -0.0314 0.0620 0.9878
4.750 0.6849 0.01176 0.00456 -0.0324 0.0546 0.9916
5.000 0.7156 0.01205 0.00481 -0.0332 0.0490 0.9953
5.250 0.7471 0.01236 0.00510 -0.0342 0.0444 0.9986
5.500 0.7719 0.01266 0.00538 -0.0339 0.0407 1.0000
5.750 0.7896 0.01295 0.00565 -0.0320 0.0382 1.0000
6.000 0.8080 0.01322 0.00592 -0.0302 0.0363 1.0000
6.250 0.8263 0.01352 0.00623 -0.0284 0.0346 1.0000
6.500 0.8442 0.01389 0.00658 -0.0266 0.0331 1.0000
6.750 0.8629 0.01422 0.00692 -0.0249 0.0322 1.0000
7.000 0.8817 0.01455 0.00728 -0.0233 0.0311 1.0000
7.250 0.9004 0.01490 0.00766 -0.0217 0.0303 1.0000
7.500 0.9190 0.01528 0.00804 -0.0200 0.0293 1.0000
7.750 0.9371 0.01571 0.00847 -0.0184 0.0284 1.0000
8.000 0.9542 0.01621 0.00899 -0.0166 0.0276 1.0000
8.250 0.9727 0.01662 0.00943 -0.0150 0.0271 1.0000
8.500 0.9906 0.01707 0.00992 -0.0134 0.0266 1.0000
8.750 1.0081 0.01753 0.01043 -0.0117 0.0260 1.0000
9.000 1.0245 0.01803 0.01096 -0.0099 0.0255 1.0000
9.250 1.0397 0.01852 0.01149 -0.0078 0.0250 1.0000
9.500 1.0546 0.01903 0.01204 -0.0058 0.0246 1.0000
9.750 1.0691 0.01958 0.01263 -0.0038 0.0243 1.0000
10.000 1.0830 0.02021 0.01329 -0.0017 0.0239 1.0000
10.250 1.0957 0.02097 0.01407 0.0004 0.0235 1.0000
10.500 1.1083 0.02178 0.01492 0.0024 0.0232 1.0000
10.750 1.1229 0.02244 0.01567 0.0040 0.0229 1.0000
11.000 1.1373 0.02315 0.01646 0.0057 0.0226 1.0000
11.250 1.1510 0.02391 0.01730 0.0073 0.0223 1.0000
11.500 1.1642 0.02474 0.01821 0.0090 0.0219 1.0000
11.750 1.1768 0.02562 0.01917 0.0106 0.0217 1.0000
12.000 1.1888 0.02655 0.02018 0.0121 0.0214 1.0000
12.250 1.2003 0.02754 0.02126 0.0137 0.0211 1.0000
12.500 1.2115 0.02854 0.02233 0.0151 0.0209 1.0000
12.750 1.2217 0.02966 0.02354 0.0166 0.0207 1.0000
13.000 1.2313 0.03083 0.02478 0.0179 0.0205 1.0000
13.250 1.2401 0.03207 0.02611 0.0193 0.0202 1.0000
13.500 1.2483 0.03339 0.02750 0.0205 0.0200 1.0000
13.750 1.2548 0.03492 0.02911 0.0217 0.0199 1.0000
14.000 1.2603 0.03656 0.03084 0.0229 0.0197 1.0000
14.250 1.2642 0.03840 0.03277 0.0239 0.0195 1.0000
14.500 1.2652 0.04064 0.03513 0.0250 0.0194 1.0000
14.750 1.2679 0.04268 0.03730 0.0257 0.0192 1.0000
15.000 1.2691 0.04494 0.03971 0.0263 0.0191 1.0000
15.250 1.2690 0.04741 0.04234 0.0266 0.0190 1.0000
15.500 1.2674 0.05012 0.04520 0.0267 0.0188 1.0000
15.750 1.2635 0.05323 0.04847 0.0266 0.0187 1.0000
16.000 1.2579 0.05670 0.05210 0.0261 0.0185 1.0000
16.250 1.2509 0.06050 0.05606 0.0252 0.0184 1.0000
16.500 1.2405 0.06501 0.06075 0.0238 0.0183 1.0000
16.750 1.2294 0.06994 0.06585 0.0218 0.0182 1.0000
17.000 1.2152 0.07561 0.07170 0.0192 0.0181 1.0000
17.250 1.1969 0.08239 0.07866 0.0157 0.0181 1.0000
17.500 1.1728 0.09077 0.08723 0.0109 0.0181 1.0000
17.750 1.1409 0.10137 0.09806 0.0045 0.0181 1.0000
18.000 1.0852 0.11838 0.11536 -0.0061 0.0182 1.0000
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