RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 500,000 Max Cl/Cd: 90.8 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf34-il-500000.txt Download as CSV file: xf-raf34-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7189 0.06057 0.05798 -0.0483 1.0000 0.0267
-11.750 -0.7973 0.04881 0.04580 -0.0536 1.0000 0.0256
-11.500 -0.8259 0.04488 0.04164 -0.0513 1.0000 0.0257
-11.250 -0.8302 0.04350 0.04017 -0.0486 1.0000 0.0263
-11.000 -0.8569 0.04024 0.03665 -0.0431 1.0000 0.0263
-10.750 -0.8627 0.03806 0.03424 -0.0396 1.0000 0.0268
-10.500 -0.8686 0.03542 0.03131 -0.0359 1.0000 0.0272
-10.250 -0.8674 0.03342 0.02902 -0.0326 1.0000 0.0277
-10.000 -0.8617 0.03183 0.02715 -0.0296 1.0000 0.0282
-9.750 -0.8527 0.03075 0.02583 -0.0268 1.0000 0.0285
-9.500 -0.8509 0.02729 0.02205 -0.0235 1.0000 0.0291
-9.250 -0.8364 0.02585 0.02057 -0.0218 1.0000 0.0298
-9.000 -0.8204 0.02496 0.01963 -0.0200 1.0000 0.0304
-8.750 -0.8037 0.02426 0.01892 -0.0183 1.0000 0.0312
-8.500 -0.7738 0.02299 0.01751 -0.0194 0.9874 0.0320
-8.250 -0.7355 0.02158 0.01590 -0.0221 0.9700 0.0328
-8.000 -0.6927 0.02044 0.01456 -0.0256 0.9491 0.0337
-7.750 -0.6492 0.01987 0.01378 -0.0291 0.9249 0.0344
-7.500 -0.6191 0.01774 0.01144 -0.0300 0.8989 0.0353
-7.250 -0.5949 0.01682 0.01040 -0.0294 0.8766 0.0361
-7.000 -0.5721 0.01622 0.00969 -0.0285 0.8583 0.0367
-6.750 -0.5494 0.01571 0.00910 -0.0274 0.8424 0.0376
-6.250 -0.5035 0.01476 0.00795 -0.0254 0.8151 0.0392
-6.000 -0.4803 0.01430 0.00740 -0.0244 0.8028 0.0399
-5.750 -0.4570 0.01388 0.00689 -0.0235 0.7919 0.0406
-5.500 -0.4334 0.01353 0.00644 -0.0225 0.7810 0.0412
-5.250 -0.4111 0.01299 0.00584 -0.0214 0.7704 0.0421
-5.000 -0.3893 0.01247 0.00527 -0.0202 0.7610 0.0436
-4.750 -0.3658 0.01212 0.00487 -0.0192 0.7513 0.0450
-4.500 -0.3417 0.01183 0.00453 -0.0184 0.7423 0.0464
-4.250 -0.3173 0.01158 0.00421 -0.0176 0.7336 0.0481
-4.000 -0.2923 0.01136 0.00393 -0.0169 0.7251 0.0496
-3.750 -0.2684 0.01103 0.00358 -0.0160 0.7170 0.0540
-3.500 -0.2436 0.01078 0.00333 -0.0153 0.7088 0.0613
-3.250 -0.2209 0.01035 0.00310 -0.0143 0.7012 0.1016
-3.000 -0.1967 0.01005 0.00292 -0.0135 0.6935 0.1385
-2.750 -0.1727 0.00978 0.00275 -0.0128 0.6860 0.1722
-2.500 -0.1494 0.00943 0.00261 -0.0119 0.6789 0.2292
-2.250 -0.1263 0.00909 0.00248 -0.0110 0.6715 0.2939
-2.000 -0.1051 0.00865 0.00233 -0.0098 0.6647 0.3773
-1.750 -0.0886 0.00798 0.00220 -0.0076 0.6575 0.5197
-1.500 -0.0725 0.00751 0.00213 -0.0050 0.6512 0.6401
-1.250 -0.0531 0.00718 0.00213 -0.0030 0.6442 0.7249
-1.000 -0.0299 0.00702 0.00213 -0.0016 0.6375 0.7851
-0.750 -0.0032 0.00693 0.00216 -0.0010 0.6309 0.8327
-0.500 0.0286 0.00691 0.00222 -0.0015 0.6236 0.8686
-0.250 0.0634 0.00699 0.00229 -0.0026 0.6169 0.8967
0.000 0.1021 0.00709 0.00239 -0.0046 0.6091 0.9139
0.250 0.1360 0.00725 0.00247 -0.0057 0.6023 0.9272
0.500 0.1795 0.00741 0.00262 -0.0087 0.5941 0.9350
1.000 0.2618 0.00789 0.00298 -0.0137 0.5769 0.9495
1.250 0.2924 0.00805 0.00307 -0.0140 0.5680 0.9571
1.500 0.3333 0.00816 0.00315 -0.0167 0.5583 0.9593
1.750 0.3728 0.00828 0.00322 -0.0191 0.5485 0.9625
2.000 0.4069 0.00843 0.00331 -0.0203 0.5393 0.9682
2.250 0.4443 0.00852 0.00339 -0.0223 0.5293 0.9721
2.500 0.4837 0.00861 0.00344 -0.0247 0.5190 0.9748
2.750 0.5188 0.00869 0.00347 -0.0263 0.5085 0.9783
3.000 0.5496 0.00878 0.00356 -0.0270 0.4985 0.9829
3.250 0.5875 0.00881 0.00355 -0.0293 0.4878 0.9848
3.500 0.6241 0.00886 0.00356 -0.0312 0.4768 0.9874
3.750 0.6593 0.00890 0.00360 -0.0329 0.4655 0.9905
4.000 0.6929 0.00899 0.00366 -0.0343 0.4537 0.9938
4.250 0.7295 0.00901 0.00365 -0.0363 0.4412 0.9961
4.500 0.7653 0.00905 0.00366 -0.0382 0.4277 0.9988
4.750 0.7944 0.00914 0.00371 -0.0387 0.4129 1.0000
5.000 0.8157 0.00927 0.00381 -0.0376 0.3977 1.0000
5.250 0.8372 0.00941 0.00392 -0.0364 0.3843 1.0000
5.500 0.8586 0.00955 0.00404 -0.0353 0.3699 1.0000
5.750 0.8797 0.00973 0.00419 -0.0342 0.3545 1.0000
6.000 0.9007 0.00992 0.00435 -0.0330 0.3389 1.0000
6.250 0.9212 0.01016 0.00453 -0.0317 0.3207 1.0000
6.500 0.9417 0.01040 0.00472 -0.0305 0.3014 1.0000
6.750 0.9616 0.01069 0.00496 -0.0291 0.2806 1.0000
7.000 0.9805 0.01106 0.00523 -0.0276 0.2564 1.0000
7.250 0.9979 0.01152 0.00556 -0.0260 0.2255 1.0000
7.500 1.0128 0.01216 0.00600 -0.0239 0.1875 1.0000
7.750 1.0270 0.01284 0.00650 -0.0218 0.1527 1.0000
8.000 1.0415 0.01347 0.00701 -0.0197 0.1323 1.0000
8.250 1.0562 0.01406 0.00752 -0.0176 0.1165 1.0000
8.500 1.0710 0.01461 0.00802 -0.0155 0.0977 1.0000
9.000 1.0867 0.01646 0.00951 -0.0092 0.0487 1.0000
9.250 1.0986 0.01706 0.01015 -0.0067 0.0446 1.0000
9.500 1.1049 0.01792 0.01101 -0.0033 0.0407 1.0000
9.750 1.1164 0.01845 0.01161 -0.0007 0.0385 1.0000
10.000 1.1227 0.01912 0.01232 0.0026 0.0364 1.0000
10.250 1.1200 0.01990 0.01312 0.0074 0.0348 1.0000
10.500 1.1172 0.02089 0.01417 0.0117 0.0333 1.0000
10.750 1.1239 0.02167 0.01503 0.0143 0.0320 1.0000
11.000 1.1284 0.02273 0.01615 0.0166 0.0308 1.0000
11.250 1.1330 0.02394 0.01740 0.0186 0.0296 1.0000
11.500 1.1335 0.02559 0.01909 0.0205 0.0284 1.0000
11.750 1.1328 0.02751 0.02108 0.0222 0.0274 1.0000
12.000 1.1415 0.02881 0.02247 0.0231 0.0265 1.0000
12.250 1.1459 0.03052 0.02426 0.0241 0.0259 1.0000
12.500 1.1515 0.03221 0.02600 0.0249 0.0248 1.0000
12.750 1.1556 0.03409 0.02793 0.0255 0.0242 1.0000
13.000 1.1554 0.03641 0.03028 0.0261 0.0233 1.0000
13.250 1.1516 0.03908 0.03302 0.0269 0.0228 1.0000
13.500 1.1551 0.04117 0.03520 0.0273 0.0224 1.0000
13.750 1.1596 0.04322 0.03733 0.0276 0.0219 1.0000
14.000 1.1641 0.04530 0.03950 0.0277 0.0212 1.0000
14.250 1.1668 0.04760 0.04187 0.0277 0.0205 1.0000
14.500 1.1695 0.04992 0.04426 0.0277 0.0202 1.0000
14.750 1.1710 0.05244 0.04683 0.0277 0.0198 1.0000
15.000 1.1723 0.05503 0.04948 0.0275 0.0194 1.0000
15.250 1.1714 0.05785 0.05232 0.0274 0.0188 1.0000
15.500 1.1702 0.06058 0.05512 0.0277 0.0184 1.0000
15.750 1.1721 0.06335 0.05800 0.0272 0.0182 1.0000
16.000 1.1738 0.06614 0.06089 0.0267 0.0179 1.0000
16.250 1.1744 0.06913 0.06398 0.0261 0.0176 1.0000
16.500 1.1746 0.07223 0.06718 0.0254 0.0173 1.0000
16.750 1.1741 0.07548 0.07053 0.0246 0.0169 1.0000
17.000 1.1735 0.07886 0.07400 0.0234 0.0166 1.0000
17.250 1.1727 0.08214 0.07737 0.0226 0.0165 1.0000
17.500 1.1705 0.08584 0.08114 0.0213 0.0160 1.0000
17.750 1.1688 0.08940 0.08477 0.0202 0.0159 1.0000
18.000 1.1676 0.09298 0.08842 0.0188 0.0156 1.0000
18.250 1.1657 0.09654 0.09202 0.0176 0.0153 1.0000
18.500 1.1601 0.10030 0.09587 0.0170 0.0150 1.0000
18.750 1.1544 0.10476 0.10044 0.0152 0.0149 1.0000
19.000 1.1458 0.10991 0.10574 0.0129 0.0148 1.0000
19.250 1.1362 0.11544 0.11143 0.0101 0.0147 1.0000
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