RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: RAF 30 AIRFOIL (raf30-il) Reynolds number: 50,000 Max Cl/Cd: 28.37 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30-il-50000.txt Download as CSV file: xf-raf30-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6085 0.11591 0.10812 -0.0086 1.0000 0.2066
-11.000 -0.6171 0.10468 0.09690 -0.0140 1.0000 0.1732
-10.750 -0.7480 0.08047 0.07292 -0.0337 1.0000 0.1465
-10.500 -0.7659 0.07498 0.06741 -0.0345 1.0000 0.1451
-10.250 -0.7911 0.07004 0.06243 -0.0340 1.0000 0.1434
-10.000 -0.8199 0.06553 0.05779 -0.0318 1.0000 0.1418
-9.750 -0.8437 0.06107 0.05310 -0.0294 1.0000 0.1406
-9.500 -0.8579 0.05705 0.04879 -0.0269 1.0000 0.1403
-9.250 -0.8657 0.05327 0.04468 -0.0243 1.0000 0.1406
-9.000 -0.8679 0.04973 0.04077 -0.0216 1.0000 0.1413
-8.750 -0.8657 0.04645 0.03707 -0.0190 1.0000 0.1427
-8.500 -0.8618 0.04358 0.03370 -0.0162 1.0000 0.1456
-8.250 -0.8475 0.04090 0.03088 -0.0146 1.0000 0.1506
-8.000 -0.8307 0.03865 0.02848 -0.0130 1.0000 0.1568
-7.750 -0.8161 0.03620 0.02560 -0.0109 1.0000 0.1626
-7.500 -0.7944 0.03418 0.02364 -0.0098 1.0000 0.1732
-7.250 -0.7746 0.03227 0.02173 -0.0084 1.0000 0.1876
-7.000 -0.7549 0.03031 0.01979 -0.0067 1.0000 0.2078
-6.750 -0.7390 0.02861 0.01842 -0.0045 1.0000 0.2402
-6.500 -0.7287 0.02710 0.01727 -0.0013 1.0000 0.2862
-6.250 -0.7195 0.02589 0.01647 0.0023 1.0000 0.3384
-6.000 -0.7113 0.02507 0.01597 0.0063 1.0000 0.3930
-5.750 -0.7015 0.02494 0.01628 0.0106 1.0000 0.4477
-5.500 -0.6896 0.02517 0.01678 0.0151 1.0000 0.5000
-5.250 -0.6729 0.02544 0.01722 0.0191 1.0000 0.5443
-5.000 -0.6568 0.02550 0.01730 0.0228 1.0000 0.5824
-4.750 -0.6404 0.02557 0.01737 0.0263 1.0000 0.6166
-4.500 -0.6203 0.02582 0.01763 0.0296 1.0000 0.6475
-4.250 -0.5982 0.02618 0.01796 0.0327 1.0000 0.6766
-4.000 -0.5763 0.02651 0.01824 0.0358 1.0000 0.7053
-3.750 -0.5550 0.02680 0.01847 0.0389 1.0000 0.7344
-3.500 -0.5334 0.02705 0.01865 0.0417 1.0000 0.7640
-3.250 -0.4948 0.02768 0.01914 0.0422 1.0000 0.7926
-3.000 -0.4415 0.02828 0.01955 0.0397 1.0000 0.8188
-2.750 -0.4114 0.02818 0.01931 0.0395 1.0000 0.8447
-2.500 -0.3229 0.02859 0.01945 0.0299 1.0000 0.8663
-2.250 -0.2630 0.02843 0.01911 0.0240 1.0000 0.8884
-2.000 -0.2170 0.02811 0.01868 0.0199 1.0000 0.9103
-1.750 -0.1518 0.02768 0.01812 0.0122 1.0000 0.9305
-1.500 -0.0972 0.02717 0.01753 0.0059 1.0000 0.9511
-1.250 -0.0417 0.02658 0.01689 -0.0011 1.0000 0.9715
-1.000 0.0239 0.02575 0.01601 -0.0102 1.0000 0.9914
-0.750 0.0483 0.02537 0.01564 -0.0126 1.0000 1.0000
-0.500 0.0328 0.02551 0.01581 -0.0084 1.0000 1.0000
-0.250 0.0164 0.02561 0.01592 -0.0042 1.0000 1.0000
0.000 0.0000 0.02565 0.01597 0.0000 1.0000 1.0000
0.250 -0.0165 0.02561 0.01592 0.0042 1.0000 1.0000
0.500 -0.0328 0.02551 0.01581 0.0084 1.0000 1.0000
0.750 -0.0484 0.02537 0.01564 0.0126 1.0000 1.0000
1.000 -0.0232 0.02575 0.01602 0.0101 0.9912 1.0000
1.250 0.0420 0.02658 0.01688 0.0010 0.9714 1.0000
1.500 0.0972 0.02716 0.01752 -0.0059 0.9511 1.0000
1.750 0.1519 0.02767 0.01811 -0.0122 0.9304 1.0000
2.000 0.2164 0.02811 0.01867 -0.0198 0.9104 1.0000
2.250 0.2630 0.02842 0.01910 -0.0240 0.8884 1.0000
2.500 0.3231 0.02858 0.01944 -0.0299 0.8663 1.0000
2.750 0.4101 0.02819 0.01933 -0.0394 0.8448 1.0000
3.000 0.4414 0.02827 0.01955 -0.0397 0.8188 1.0000
3.250 0.4948 0.02768 0.01914 -0.0422 0.7926 1.0000
3.500 0.5337 0.02703 0.01863 -0.0417 0.7639 1.0000
3.750 0.5549 0.02679 0.01846 -0.0389 0.7344 1.0000
4.000 0.5762 0.02651 0.01824 -0.0358 0.7054 1.0000
4.250 0.5982 0.02618 0.01796 -0.0328 0.6767 1.0000
4.500 0.6203 0.02582 0.01763 -0.0296 0.6476 1.0000
4.750 0.6405 0.02557 0.01737 -0.0264 0.6168 1.0000
5.000 0.6568 0.02550 0.01729 -0.0228 0.5825 1.0000
5.250 0.6729 0.02544 0.01723 -0.0191 0.5443 1.0000
5.500 0.6896 0.02517 0.01679 -0.0151 0.5001 1.0000
5.750 0.7015 0.02494 0.01627 -0.0106 0.4476 1.0000
6.000 0.7113 0.02507 0.01597 -0.0063 0.3930 1.0000
6.250 0.7194 0.02589 0.01646 -0.0023 0.3381 1.0000
6.500 0.7287 0.02710 0.01726 0.0013 0.2860 1.0000
6.750 0.7390 0.02861 0.01843 0.0045 0.2403 1.0000
7.000 0.7550 0.03032 0.01980 0.0067 0.2078 1.0000
7.250 0.7746 0.03227 0.02173 0.0084 0.1875 1.0000
7.500 0.7943 0.03418 0.02364 0.0099 0.1731 1.0000
7.750 0.8161 0.03619 0.02559 0.0109 0.1626 1.0000
8.000 0.8307 0.03865 0.02847 0.0130 0.1568 1.0000
8.250 0.8475 0.04093 0.03092 0.0146 0.1507 1.0000
8.500 0.8618 0.04358 0.03370 0.0162 0.1456 1.0000
8.750 0.8656 0.04647 0.03710 0.0190 0.1427 1.0000
9.000 0.8679 0.04974 0.04078 0.0216 0.1413 1.0000
9.250 0.8658 0.05328 0.04469 0.0242 0.1406 1.0000
9.500 0.8580 0.05706 0.04880 0.0269 0.1403 1.0000
9.750 0.8436 0.06112 0.05315 0.0294 0.1406 1.0000
10.000 0.8203 0.06554 0.05780 0.0318 0.1418 1.0000
10.250 0.7925 0.07006 0.06245 0.0338 0.1436 1.0000
10.500 0.7663 0.07502 0.06745 0.0345 0.1451 1.0000
10.750 0.7497 0.08047 0.07293 0.0337 0.1465 1.0000
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