RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 100,000 Max Cl/Cd: 49.09 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf34-il-100000-n5.txt Download as CSV file: xf-raf34-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 34 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6144 0.07602 0.07072 -0.0407 1.0000 0.0427
-11.000 -0.6424 0.06843 0.06305 -0.0461 1.0000 0.0424
-10.750 -0.6706 0.06285 0.05733 -0.0482 1.0000 0.0423
-10.500 -0.6964 0.05862 0.05294 -0.0474 1.0000 0.0422
-10.250 -0.7233 0.05503 0.04912 -0.0442 1.0000 0.0423
-10.000 -0.7444 0.05139 0.04512 -0.0409 1.0000 0.0427
-9.750 -0.7470 0.04851 0.04211 -0.0388 1.0000 0.0432
-9.500 -0.7424 0.04637 0.03988 -0.0369 1.0000 0.0439
-9.250 -0.7392 0.04401 0.03732 -0.0347 1.0000 0.0444
-9.000 -0.7350 0.04160 0.03467 -0.0323 1.0000 0.0449
-8.750 -0.7282 0.03940 0.03223 -0.0300 1.0000 0.0456
-8.500 -0.7193 0.03753 0.03014 -0.0278 1.0000 0.0465
-8.250 -0.7099 0.03579 0.02816 -0.0255 1.0000 0.0478
-8.000 -0.7009 0.03403 0.02613 -0.0229 1.0000 0.0489
-7.750 -0.6921 0.03237 0.02421 -0.0202 1.0000 0.0497
-7.500 -0.6699 0.03046 0.02196 -0.0200 0.9882 0.0505
-7.250 -0.6356 0.02859 0.01971 -0.0218 0.9725 0.0515
-7.000 -0.6010 0.02694 0.01797 -0.0239 0.9578 0.0531
-6.750 -0.5654 0.02577 0.01673 -0.0259 0.9433 0.0552
-6.500 -0.5293 0.02457 0.01538 -0.0279 0.9294 0.0572
-6.250 -0.4944 0.02341 0.01404 -0.0294 0.9156 0.0589
-6.000 -0.4614 0.02240 0.01287 -0.0305 0.9015 0.0607
-5.750 -0.4319 0.02149 0.01188 -0.0309 0.8874 0.0626
-5.500 -0.4053 0.02081 0.01117 -0.0308 0.8735 0.0655
-5.250 -0.3798 0.02025 0.01051 -0.0303 0.8602 0.0696
-5.000 -0.3555 0.01968 0.00985 -0.0295 0.8479 0.0740
-4.750 -0.3325 0.01916 0.00931 -0.0286 0.8359 0.0796
-4.500 -0.3099 0.01865 0.00876 -0.0275 0.8240 0.0879
-4.250 -0.2871 0.01816 0.00827 -0.0265 0.8133 0.1027
-4.000 -0.2640 0.01769 0.00783 -0.0255 0.8035 0.1257
-3.750 -0.2413 0.01724 0.00748 -0.0246 0.7927 0.1546
-3.500 -0.2183 0.01680 0.00716 -0.0237 0.7835 0.1914
-3.250 -0.1961 0.01634 0.00691 -0.0227 0.7739 0.2443
-3.000 -0.1756 0.01574 0.00666 -0.0214 0.7649 0.3287
-2.750 -0.1593 0.01482 0.00650 -0.0192 0.7564 0.4811
-2.500 -0.1356 0.01422 0.00659 -0.0177 0.7477 0.6472
-2.250 -0.0986 0.01411 0.00669 -0.0184 0.7400 0.7438
-2.000 -0.0602 0.01421 0.00678 -0.0197 0.7312 0.7953
-1.750 -0.0223 0.01435 0.00680 -0.0210 0.7235 0.8297
-1.500 0.0152 0.01453 0.00690 -0.0223 0.7144 0.8571
-1.250 0.0568 0.01482 0.00705 -0.0240 0.7068 0.8873
-1.000 0.1021 0.01516 0.00728 -0.0267 0.6975 0.9096
-0.750 0.1437 0.01537 0.00732 -0.0289 0.6899 0.9247
-0.500 0.1838 0.01552 0.00738 -0.0311 0.6802 0.9379
-0.250 0.2240 0.01563 0.00736 -0.0334 0.6722 0.9506
0.000 0.2629 0.01570 0.00735 -0.0356 0.6627 0.9621
0.250 0.3009 0.01572 0.00727 -0.0377 0.6541 0.9715
0.500 0.3381 0.01567 0.00714 -0.0398 0.6451 0.9781
0.750 0.3727 0.01565 0.00706 -0.0414 0.6361 0.9850
1.000 0.4092 0.01557 0.00690 -0.0434 0.6275 0.9911
1.250 0.4451 0.01551 0.00682 -0.0454 0.6179 0.9971
1.500 0.4741 0.01547 0.00670 -0.0458 0.6101 1.0000
1.750 0.4949 0.01551 0.00676 -0.0448 0.6004 1.0000
2.000 0.5163 0.01555 0.00673 -0.0437 0.5929 1.0000
2.250 0.5374 0.01561 0.00681 -0.0426 0.5833 1.0000
2.500 0.5588 0.01567 0.00685 -0.0415 0.5750 1.0000
2.750 0.5802 0.01575 0.00693 -0.0404 0.5659 1.0000
3.000 0.6016 0.01584 0.00702 -0.0393 0.5569 1.0000
3.250 0.6232 0.01593 0.00710 -0.0381 0.5479 1.0000
3.500 0.6443 0.01605 0.00725 -0.0369 0.5373 1.0000
3.750 0.6657 0.01615 0.00734 -0.0357 0.5275 1.0000
4.000 0.6869 0.01628 0.00748 -0.0345 0.5171 1.0000
4.250 0.7079 0.01643 0.00767 -0.0333 0.5061 1.0000
4.500 0.7291 0.01657 0.00781 -0.0320 0.4952 1.0000
4.750 0.7502 0.01671 0.00796 -0.0308 0.4845 1.0000
5.000 0.7709 0.01691 0.00820 -0.0295 0.4723 1.0000
5.250 0.7916 0.01710 0.00843 -0.0282 0.4607 1.0000
5.500 0.8122 0.01730 0.00866 -0.0268 0.4488 1.0000
5.750 0.8325 0.01752 0.00886 -0.0254 0.4363 1.0000
6.000 0.8525 0.01777 0.00917 -0.0241 0.4237 1.0000
6.250 0.8726 0.01805 0.00953 -0.0227 0.4121 1.0000
6.500 0.8927 0.01835 0.00989 -0.0213 0.4014 1.0000
7.000 0.9315 0.01900 0.01064 -0.0184 0.3777 1.0000
7.250 0.9494 0.01934 0.01103 -0.0167 0.3623 1.0000
7.500 0.9659 0.01973 0.01142 -0.0148 0.3442 1.0000
7.750 0.9811 0.02017 0.01188 -0.0128 0.3221 1.0000
8.000 0.9947 0.02069 0.01235 -0.0106 0.2994 1.0000
8.250 1.0083 0.02125 0.01292 -0.0084 0.2771 1.0000
8.500 1.0199 0.02190 0.01353 -0.0060 0.2546 1.0000
8.750 1.0300 0.02264 0.01424 -0.0035 0.2299 1.0000
9.000 1.0374 0.02349 0.01501 -0.0007 0.2062 1.0000
9.250 1.0436 0.02441 0.01586 0.0022 0.1837 1.0000
9.500 1.0465 0.02546 0.01683 0.0054 0.1640 1.0000
9.750 1.0457 0.02658 0.01787 0.0092 0.1472 1.0000
10.000 1.0421 0.02781 0.01904 0.0130 0.1337 1.0000
10.250 1.0382 0.02928 0.02045 0.0162 0.1216 1.0000
10.500 1.0362 0.03089 0.02209 0.0187 0.1091 1.0000
10.750 1.0357 0.03261 0.02384 0.0207 0.0956 1.0000
11.000 1.0354 0.03446 0.02571 0.0223 0.0822 1.0000
11.250 1.0343 0.03651 0.02775 0.0236 0.0732 1.0000
11.500 1.0319 0.03881 0.03003 0.0247 0.0669 1.0000
11.750 1.0289 0.04127 0.03249 0.0255 0.0623 1.0000
12.000 1.0252 0.04392 0.03514 0.0262 0.0590 1.0000
12.250 1.0243 0.04639 0.03771 0.0267 0.0561 1.0000
12.500 1.0216 0.04911 0.04049 0.0271 0.0532 1.0000
12.750 1.0174 0.05205 0.04345 0.0273 0.0510 1.0000
13.000 1.0163 0.05473 0.04622 0.0276 0.0486 1.0000
13.250 1.0173 0.05723 0.04883 0.0278 0.0467 1.0000
13.500 1.0175 0.05987 0.05156 0.0279 0.0447 1.0000
13.750 1.0171 0.06261 0.05435 0.0279 0.0430 1.0000
14.000 1.0176 0.06518 0.05689 0.0282 0.0413 1.0000
14.250 1.0202 0.06780 0.05968 0.0281 0.0397 1.0000
14.500 1.0218 0.07058 0.06260 0.0280 0.0381 1.0000
14.750 1.0240 0.07330 0.06542 0.0278 0.0368 1.0000
15.000 1.0262 0.07606 0.06826 0.0276 0.0358 1.0000
15.250 1.0287 0.07877 0.07103 0.0274 0.0347 1.0000
15.500 1.0327 0.08125 0.07350 0.0275 0.0335 1.0000
15.750 1.0283 0.08532 0.07781 0.0262 0.0327 1.0000
16.000 1.0242 0.08943 0.08212 0.0249 0.0319 1.0000
16.250 1.0176 0.09401 0.08689 0.0232 0.0311 1.0000
16.500 1.0109 0.09872 0.09178 0.0214 0.0305 1.0000
16.750 1.0030 0.10379 0.09702 0.0192 0.0300 1.0000
17.000 0.9937 0.10924 0.10263 0.0167 0.0296 1.0000
17.250 0.9819 0.11534 0.10891 0.0138 0.0294 1.0000
17.500 0.9676 0.12216 0.11590 0.0102 0.0290 1.0000
17.750 0.9466 0.13089 0.12483 0.0053 0.0291 1.0000
18.000 0.9068 0.14493 0.13914 -0.0029 0.0296 1.0000
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