RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 AIRFOIL (raf30-il) Reynolds number: 100,000 Max Cl/Cd: 39.14 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30-il-100000-n5.txt Download as CSV file: xf-raf30-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7920 0.09677 0.09105 -0.0258 1.0000 0.0390
-14.000 -0.8612 0.08021 0.07415 -0.0371 1.0000 0.0374
-13.750 -0.8951 0.07201 0.06569 -0.0419 1.0000 0.0371
-13.500 -0.9162 0.06646 0.05993 -0.0444 1.0000 0.0373
-13.250 -0.9329 0.06190 0.05516 -0.0458 1.0000 0.0376
-13.000 -0.9460 0.05809 0.05115 -0.0464 1.0000 0.0381
-12.750 -0.9574 0.05464 0.04748 -0.0462 1.0000 0.0385
-12.500 -0.9666 0.05163 0.04425 -0.0455 1.0000 0.0392
-12.250 -0.9738 0.04888 0.04125 -0.0442 1.0000 0.0399
-12.000 -0.9786 0.04636 0.03847 -0.0424 1.0000 0.0406
-11.750 -0.9803 0.04414 0.03597 -0.0404 1.0000 0.0413
-11.500 -0.9813 0.04226 0.03379 -0.0378 1.0000 0.0421
-11.250 -0.9720 0.04025 0.03176 -0.0364 1.0000 0.0434
-11.000 -0.9635 0.03876 0.03023 -0.0346 1.0000 0.0446
-10.750 -0.9548 0.03733 0.02871 -0.0326 1.0000 0.0459
-10.500 -0.9441 0.03585 0.02707 -0.0307 1.0000 0.0471
-10.250 -0.9323 0.03449 0.02555 -0.0289 1.0000 0.0488
-10.000 -0.9191 0.03321 0.02406 -0.0271 1.0000 0.0505
-9.750 -0.9045 0.03182 0.02259 -0.0256 1.0000 0.0521
-9.500 -0.8908 0.03058 0.02135 -0.0239 1.0000 0.0536
-9.250 -0.8771 0.02948 0.02020 -0.0221 1.0000 0.0551
-9.000 -0.8633 0.02849 0.01915 -0.0202 1.0000 0.0573
-8.750 -0.8491 0.02754 0.01810 -0.0182 1.0000 0.0598
-8.500 -0.8350 0.02661 0.01709 -0.0162 1.0000 0.0620
-8.250 -0.8236 0.02560 0.01611 -0.0138 1.0000 0.0644
-8.000 -0.8106 0.02474 0.01522 -0.0116 1.0000 0.0672
-7.750 -0.7971 0.02393 0.01433 -0.0093 1.0000 0.0708
-7.500 -0.7840 0.02312 0.01351 -0.0070 1.0000 0.0753
-7.250 -0.7704 0.02234 0.01275 -0.0048 1.0000 0.0826
-7.000 -0.7571 0.02154 0.01200 -0.0025 1.0000 0.0923
-6.750 -0.7436 0.02076 0.01128 -0.0002 1.0000 0.1063
-6.500 -0.7297 0.02003 0.01059 0.0020 1.0000 0.1245
-6.250 -0.7158 0.01935 0.01000 0.0042 1.0000 0.1454
-6.000 -0.7020 0.01870 0.00947 0.0065 1.0000 0.1704
-5.750 -0.6885 0.01809 0.00903 0.0087 1.0000 0.2006
-5.500 -0.6752 0.01754 0.00864 0.0110 1.0000 0.2355
-5.250 -0.6618 0.01706 0.00832 0.0134 1.0000 0.2732
-5.000 -0.6488 0.01662 0.00804 0.0157 1.0000 0.3118
-4.750 -0.6337 0.01619 0.00782 0.0177 0.9991 0.3548
-4.500 -0.6005 0.01575 0.00763 0.0161 0.9904 0.4095
-4.250 -0.5666 0.01545 0.00750 0.0146 0.9819 0.4560
-4.000 -0.5322 0.01525 0.00736 0.0131 0.9732 0.4913
-3.750 -0.4990 0.01507 0.00721 0.0120 0.9636 0.5213
-3.500 -0.4651 0.01492 0.00708 0.0107 0.9547 0.5494
-3.250 -0.4295 0.01479 0.00696 0.0093 0.9465 0.5785
-3.000 -0.3977 0.01469 0.00691 0.0087 0.9366 0.6093
-2.750 -0.3600 0.01460 0.00688 0.0070 0.9300 0.6374
-2.500 -0.3284 0.01451 0.00678 0.0064 0.9192 0.6578
-2.250 -0.2927 0.01441 0.00668 0.0051 0.9108 0.6750
-2.000 -0.2585 0.01433 0.00658 0.0041 0.9011 0.6912
-1.750 -0.2253 0.01425 0.00650 0.0033 0.8907 0.7068
-1.500 -0.1888 0.01417 0.00640 0.0019 0.8821 0.7221
-1.250 -0.1582 0.01412 0.00634 0.0016 0.8699 0.7366
-1.000 -0.1258 0.01408 0.00630 0.0011 0.8585 0.7502
-0.750 -0.0923 0.01403 0.00625 0.0004 0.8474 0.7638
-0.500 -0.0600 0.01400 0.00620 -0.0001 0.8347 0.7773
-0.250 -0.0299 0.01397 0.00617 -0.0001 0.8202 0.7911
0.000 0.0000 0.01397 0.00616 0.0000 0.8054 0.8054
0.250 0.0299 0.01397 0.00617 0.0001 0.7910 0.8202
0.500 0.0600 0.01400 0.00620 0.0001 0.7772 0.8347
0.750 0.0923 0.01403 0.00625 -0.0004 0.7638 0.8474
1.000 0.1258 0.01408 0.00630 -0.0011 0.7503 0.8585
1.250 0.1582 0.01412 0.00634 -0.0016 0.7367 0.8699
1.500 0.1889 0.01417 0.00640 -0.0019 0.7221 0.8821
1.750 0.2254 0.01425 0.00650 -0.0033 0.7068 0.8907
2.000 0.2585 0.01433 0.00658 -0.0041 0.6912 0.9010
2.250 0.2927 0.01441 0.00668 -0.0051 0.6749 0.9107
2.500 0.3285 0.01451 0.00678 -0.0064 0.6578 0.9192
2.750 0.3600 0.01460 0.00688 -0.0070 0.6374 0.9300
3.000 0.3978 0.01469 0.00691 -0.0087 0.6091 0.9366
3.250 0.4295 0.01479 0.00697 -0.0093 0.5783 0.9465
3.500 0.4651 0.01492 0.00708 -0.0107 0.5493 0.9547
3.750 0.4990 0.01507 0.00721 -0.0120 0.5211 0.9636
4.000 0.5322 0.01525 0.00736 -0.0131 0.4912 0.9732
4.250 0.5665 0.01546 0.00749 -0.0146 0.4546 0.9819
4.500 0.6005 0.01574 0.00763 -0.0161 0.4098 0.9904
4.750 0.6337 0.01619 0.00782 -0.0177 0.3539 0.9991
5.000 0.6488 0.01662 0.00804 -0.0157 0.3115 1.0000
5.250 0.6618 0.01706 0.00832 -0.0134 0.2724 1.0000
5.500 0.6752 0.01754 0.00864 -0.0110 0.2352 1.0000
5.750 0.6886 0.01809 0.00903 -0.0087 0.2006 1.0000
6.000 0.7020 0.01870 0.00947 -0.0065 0.1699 1.0000
6.250 0.7158 0.01935 0.01000 -0.0042 0.1452 1.0000
6.500 0.7298 0.02003 0.01059 -0.0020 0.1244 1.0000
6.750 0.7436 0.02077 0.01128 0.0002 0.1060 1.0000
7.000 0.7572 0.02154 0.01200 0.0025 0.0924 1.0000
7.250 0.7704 0.02234 0.01275 0.0048 0.0826 1.0000
7.500 0.7841 0.02311 0.01351 0.0070 0.0755 1.0000
7.750 0.7971 0.02393 0.01434 0.0093 0.0707 1.0000
8.000 0.8107 0.02474 0.01522 0.0116 0.0672 1.0000
8.250 0.8237 0.02560 0.01611 0.0138 0.0645 1.0000
8.500 0.8352 0.02660 0.01708 0.0162 0.0621 1.0000
8.750 0.8492 0.02754 0.01810 0.0182 0.0598 1.0000
9.000 0.8634 0.02849 0.01914 0.0201 0.0573 1.0000
9.250 0.8772 0.02948 0.02021 0.0220 0.0552 1.0000
9.500 0.8909 0.03057 0.02134 0.0239 0.0536 1.0000
9.750 0.9045 0.03182 0.02259 0.0256 0.0520 1.0000
10.000 0.9191 0.03320 0.02406 0.0271 0.0505 1.0000
10.250 0.9324 0.03450 0.02556 0.0289 0.0487 1.0000
10.500 0.9442 0.03586 0.02708 0.0307 0.0471 1.0000
10.750 0.9550 0.03733 0.02870 0.0326 0.0459 1.0000
11.000 0.9641 0.03881 0.03029 0.0345 0.0447 1.0000
11.250 0.9722 0.04027 0.03179 0.0364 0.0434 1.0000
11.500 0.9824 0.04228 0.03380 0.0377 0.0422 1.0000
11.750 0.9804 0.04414 0.03598 0.0403 0.0413 1.0000
12.000 0.9785 0.04635 0.03846 0.0424 0.0405 1.0000
12.250 0.9741 0.04886 0.04123 0.0441 0.0398 1.0000
12.500 0.9670 0.05162 0.04424 0.0454 0.0392 1.0000
12.750 0.9578 0.05468 0.04752 0.0462 0.0386 1.0000
13.000 0.9469 0.05802 0.05107 0.0463 0.0379 1.0000
13.250 0.9341 0.06180 0.05505 0.0458 0.0375 1.0000
13.500 0.9175 0.06635 0.05981 0.0444 0.0372 1.0000
13.750 0.8947 0.07220 0.06589 0.0417 0.0373 1.0000
14.000 0.8643 0.07983 0.07376 0.0373 0.0374 1.0000
14.250 0.7937 0.09664 0.09091 0.0257 0.0389 1.0000
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