BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 500,000 Max Cl/Cd: 72.78 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr1-il-500000.txt Download as CSV file: xf-vr1-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5537 0.08877 0.08624 -0.0409 1.0000 0.0306
-11.000 -0.5542 0.08511 0.08260 -0.0422 1.0000 0.0307
-10.750 -0.5496 0.08332 0.08082 -0.0421 1.0000 0.0311
-10.500 -0.5585 0.07679 0.07431 -0.0463 1.0000 0.0313
-10.250 -0.6151 0.06145 0.05881 -0.0600 1.0000 0.0312
-10.000 -0.6494 0.05681 0.05403 -0.0595 1.0000 0.0312
-9.750 -0.6666 0.05467 0.05184 -0.0560 1.0000 0.0313
-9.500 -0.6728 0.05265 0.04977 -0.0536 1.0000 0.0316
-9.250 -0.6794 0.05064 0.04771 -0.0507 1.0000 0.0319
-9.000 -0.6885 0.04871 0.04570 -0.0469 1.0000 0.0322
-8.750 -0.7016 0.04705 0.04396 -0.0419 1.0000 0.0325
-8.500 -0.6896 0.04361 0.04026 -0.0428 0.9968 0.0342
-8.250 -0.6792 0.03796 0.03399 -0.0444 0.9903 0.0371
-8.000 -0.6516 0.03594 0.03194 -0.0462 0.9871 0.0379
-7.750 -0.6225 0.03404 0.02993 -0.0480 0.9845 0.0393
-7.500 -0.6034 0.03126 0.02664 -0.0483 0.9779 0.0440
-7.250 -0.5728 0.02948 0.02488 -0.0500 0.9752 0.0453
-7.000 -0.5457 0.02296 0.01699 -0.0486 0.9721 0.0303
-6.500 -0.4885 0.02178 0.01607 -0.0516 0.9627 0.0443
-6.000 -0.4203 0.01572 0.00932 -0.0523 0.9567 0.0279
-5.750 -0.3931 0.01495 0.00850 -0.0522 0.9492 0.0283
-5.500 -0.3627 0.01413 0.00762 -0.0528 0.9439 0.0285
-5.250 -0.3370 0.01348 0.00693 -0.0523 0.9359 0.0287
-5.000 -0.3106 0.01288 0.00629 -0.0520 0.9287 0.0290
-4.750 -0.2861 0.01240 0.00576 -0.0513 0.9207 0.0294
-4.500 -0.2613 0.01196 0.00529 -0.0505 0.9128 0.0298
-4.250 -0.2368 0.01159 0.00487 -0.0498 0.9050 0.0301
-4.000 -0.2137 0.01107 0.00431 -0.0488 0.8971 0.0308
-3.750 -0.1893 0.01068 0.00391 -0.0480 0.8898 0.0321
-3.500 -0.1645 0.01041 0.00361 -0.0473 0.8819 0.0336
-3.250 -0.1384 0.01018 0.00333 -0.0468 0.8754 0.0350
-3.000 -0.1134 0.00995 0.00307 -0.0462 0.8676 0.0367
-2.750 -0.0872 0.00973 0.00283 -0.0457 0.8611 0.0407
-2.500 -0.0631 0.00937 0.00261 -0.0449 0.8537 0.0704
-2.250 -0.0451 0.00831 0.00233 -0.0434 0.8464 0.2729
-2.000 -0.0268 0.00749 0.00219 -0.0418 0.8393 0.4529
-1.750 -0.0068 0.00698 0.00212 -0.0403 0.8321 0.5739
-1.500 0.0156 0.00670 0.00211 -0.0389 0.8261 0.6625
-1.250 0.0391 0.00653 0.00212 -0.0378 0.8188 0.7154
-1.000 0.0641 0.00644 0.00213 -0.0369 0.8127 0.7601
-0.750 0.0891 0.00638 0.00217 -0.0360 0.8063 0.7968
-0.500 0.1145 0.00635 0.00221 -0.0351 0.7996 0.8277
-0.250 0.1409 0.00636 0.00225 -0.0344 0.7939 0.8542
0.000 0.1660 0.00637 0.00234 -0.0334 0.7869 0.8803
0.250 0.1928 0.00641 0.00239 -0.0328 0.7799 0.8986
0.500 0.2190 0.00644 0.00242 -0.0321 0.7703 0.9127
0.750 0.2464 0.00649 0.00243 -0.0315 0.7604 0.9250
1.000 0.2758 0.00653 0.00247 -0.0316 0.7501 0.9340
1.250 0.3034 0.00658 0.00249 -0.0312 0.7388 0.9442
1.500 0.3365 0.00664 0.00250 -0.0320 0.7250 0.9500
1.750 0.3643 0.00669 0.00251 -0.0318 0.7081 0.9585
2.000 0.4010 0.00677 0.00254 -0.0335 0.6885 0.9621
2.250 0.4376 0.00687 0.00258 -0.0352 0.6685 0.9665
2.500 0.4696 0.00699 0.00263 -0.0359 0.6451 0.9724
2.750 0.5074 0.00715 0.00269 -0.0380 0.6104 0.9751
3.000 0.5415 0.00744 0.00275 -0.0394 0.5529 0.9794
3.250 0.5698 0.00821 0.00297 -0.0399 0.4263 0.9856
3.500 0.5983 0.00974 0.00351 -0.0413 0.2178 0.9918
3.750 0.6328 0.01063 0.00392 -0.0434 0.1234 0.9966
4.000 0.6692 0.01108 0.00421 -0.0457 0.0974 0.9999
4.250 0.6859 0.01138 0.00444 -0.0437 0.0848 1.0000
4.500 0.7025 0.01162 0.00465 -0.0416 0.0756 1.0000
4.750 0.7186 0.01190 0.00491 -0.0394 0.0676 1.0000
5.000 0.7336 0.01228 0.00523 -0.0370 0.0609 1.0000
5.250 0.7507 0.01254 0.00549 -0.0350 0.0563 1.0000
5.500 0.7650 0.01301 0.00591 -0.0324 0.0519 1.0000
5.750 0.7830 0.01327 0.00620 -0.0305 0.0492 1.0000
6.000 0.8004 0.01361 0.00653 -0.0286 0.0466 1.0000
6.250 0.8134 0.01428 0.00717 -0.0259 0.0441 1.0000
6.500 0.8321 0.01461 0.00754 -0.0242 0.0429 1.0000
6.750 0.8499 0.01501 0.00796 -0.0223 0.0413 1.0000
7.000 0.8674 0.01546 0.00843 -0.0204 0.0401 1.0000
7.250 0.8847 0.01595 0.00891 -0.0186 0.0389 1.0000
7.500 0.8985 0.01680 0.00976 -0.0162 0.0375 1.0000
7.750 0.9166 0.01735 0.01035 -0.0146 0.0366 1.0000
8.000 0.9351 0.01788 0.01094 -0.0130 0.0358 1.0000
8.250 0.9536 0.01846 0.01156 -0.0115 0.0350 1.0000
8.500 0.9720 0.01908 0.01222 -0.0100 0.0342 1.0000
8.750 0.9904 0.01973 0.01290 -0.0086 0.0335 1.0000
9.000 1.0088 0.02039 0.01358 -0.0072 0.0328 1.0000
9.250 1.0271 0.02128 0.01448 -0.0059 0.0322 1.0000
9.500 1.0488 0.02309 0.01632 -0.0054 0.0313 1.0000
9.750 1.0670 0.02371 0.01706 -0.0040 0.0310 1.0000
10.000 1.0846 0.02444 0.01789 -0.0026 0.0305 1.0000
10.250 1.1022 0.02538 0.01894 -0.0012 0.0300 1.0000
10.500 1.1193 0.02645 0.02013 0.0002 0.0296 1.0000
10.750 1.1349 0.02753 0.02132 0.0018 0.0291 1.0000
11.000 1.1497 0.02876 0.02268 0.0034 0.0287 1.0000
11.250 1.1627 0.02981 0.02382 0.0053 0.0283 1.0000
11.500 1.1741 0.03103 0.02516 0.0073 0.0280 1.0000
11.750 1.1839 0.03219 0.02642 0.0094 0.0276 1.0000
12.000 1.1927 0.03368 0.02804 0.0114 0.0274 1.0000
12.250 1.2013 0.03499 0.02941 0.0133 0.0270 1.0000
12.500 1.2078 0.03720 0.03174 0.0150 0.0266 1.0000
12.750 1.2013 0.04091 0.03572 0.0177 0.0263 1.0000
13.000 1.1948 0.04265 0.03767 0.0206 0.0262 1.0000
13.250 1.1862 0.04477 0.04001 0.0231 0.0261 1.0000
13.500 1.1751 0.04760 0.04306 0.0252 0.0260 1.0000
13.750 1.1608 0.05091 0.04660 0.0268 0.0259 1.0000
14.000 1.1434 0.05471 0.05062 0.0277 0.0259 1.0000
14.250 1.1219 0.05925 0.05539 0.0278 0.0258 1.0000
14.500 1.0975 0.06469 0.06103 0.0270 0.0259 1.0000
14.750 1.0703 0.07091 0.06746 0.0249 0.0259 1.0000
15.000 1.0402 0.07837 0.07511 0.0214 0.0260 1.0000
15.250 1.0074 0.08737 0.08428 0.0164 0.0262 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-1 AIRFOIL (vr1-il)