RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 100,000 Max Cl/Cd: 48.22 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf34-il-100000.txt Download as CSV file: xf-raf34-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4741 0.13143 0.12610 -0.0062 1.0000 0.1176
-11.750 -0.4825 0.12837 0.12309 -0.0095 1.0000 0.1221
-11.500 -0.5242 0.12594 0.12081 -0.0178 1.0000 0.1239
-11.250 -0.4717 0.12031 0.11507 -0.0110 1.0000 0.1278
-11.000 -0.4632 0.11713 0.11189 -0.0113 1.0000 0.1325
-10.750 -0.4832 0.11389 0.10875 -0.0161 1.0000 0.1380
-10.500 -0.4969 0.10905 0.10400 -0.0196 1.0000 0.1401
-10.250 -0.4668 0.10564 0.10053 -0.0164 1.0000 0.1430
-10.000 -0.4587 0.10248 0.09738 -0.0165 1.0000 0.1476
-9.750 -0.5042 0.09830 0.09337 -0.0248 1.0000 0.1541
-9.500 -0.4854 0.09374 0.08882 -0.0229 1.0000 0.1566
-9.250 -0.4618 0.09140 0.08645 -0.0204 1.0000 0.1620
-9.000 -0.4961 0.08669 0.08189 -0.0265 1.0000 0.1689
-8.750 -0.4903 0.08258 0.07783 -0.0261 1.0000 0.1731
-8.500 -0.4761 0.08012 0.07537 -0.0247 1.0000 0.1793
-8.250 -0.5403 0.07552 0.07087 -0.0286 1.0000 0.1847
-8.000 -0.5182 0.07194 0.06736 -0.0270 1.0000 0.1900
-7.750 -0.5200 0.06905 0.06450 -0.0262 1.0000 0.1963
-7.500 -0.6176 0.05113 0.04559 -0.0272 1.0000 0.1126
-7.250 -0.6522 0.04534 0.03886 -0.0193 1.0000 0.0941
-7.000 -0.6599 0.04329 0.03676 -0.0147 1.0000 0.0933
-6.750 -0.6664 0.04134 0.03469 -0.0104 1.0000 0.0922
-6.500 -0.6631 0.03890 0.03200 -0.0077 0.9984 0.0909
-6.250 -0.6293 0.03514 0.02768 -0.0101 0.9887 0.0896
-6.000 -0.5926 0.03250 0.02451 -0.0126 0.9793 0.0914
-5.750 -0.5535 0.03015 0.02166 -0.0150 0.9707 0.0929
-5.500 -0.5155 0.02821 0.01928 -0.0171 0.9610 0.0941
-5.250 -0.4688 0.02600 0.01688 -0.0209 0.9551 0.0969
-5.000 -0.4298 0.02478 0.01564 -0.0233 0.9454 0.1025
-4.750 -0.3785 0.02340 0.01401 -0.0275 0.9401 0.1088
-4.500 -0.3403 0.02196 0.01275 -0.0296 0.9305 0.1166
-4.250 -0.2948 0.02063 0.01150 -0.0330 0.9241 0.1335
-4.000 -0.2663 0.01942 0.01054 -0.0331 0.9128 0.1652
-3.750 -0.2409 0.01811 0.00977 -0.0328 0.9026 0.2409
-3.500 -0.2165 0.01693 0.00926 -0.0323 0.8929 0.3581
-3.250 -0.2044 0.01585 0.00927 -0.0289 0.8811 0.5650
-3.000 -0.1441 0.01580 0.01001 -0.0315 0.8765 0.8079
-2.750 -0.0861 0.01672 0.01077 -0.0344 0.8679 0.8680
-2.500 -0.0277 0.01734 0.01112 -0.0381 0.8604 0.8955
-2.250 0.0350 0.01790 0.01144 -0.0434 0.8504 0.9148
-2.000 0.0949 0.01822 0.01154 -0.0485 0.8410 0.9347
-1.750 0.1694 0.01836 0.01146 -0.0565 0.8310 0.9622
-1.500 0.2320 0.01810 0.01104 -0.0633 0.8196 0.9836
-1.250 0.2844 0.01758 0.01036 -0.0686 0.8085 0.9968
-1.000 0.3097 0.01742 0.01009 -0.0687 0.7973 1.0000
-0.750 0.3263 0.01744 0.01004 -0.0674 0.7851 1.0000
-0.500 0.3435 0.01748 0.01000 -0.0659 0.7743 1.0000
-0.250 0.3613 0.01748 0.00989 -0.0643 0.7646 1.0000
0.000 0.3790 0.01757 0.00995 -0.0630 0.7529 1.0000
0.250 0.3972 0.01764 0.00996 -0.0615 0.7429 1.0000
0.500 0.4160 0.01768 0.00991 -0.0600 0.7332 1.0000
0.750 0.4344 0.01781 0.01004 -0.0587 0.7220 1.0000
1.000 0.4539 0.01788 0.01003 -0.0571 0.7130 1.0000
1.250 0.4731 0.01799 0.01011 -0.0557 0.7025 1.0000
1.500 0.4923 0.01815 0.01025 -0.0544 0.6922 1.0000
1.750 0.5131 0.01816 0.01020 -0.0529 0.6837 1.0000
2.000 0.5321 0.01839 0.01045 -0.0516 0.6724 1.0000
2.250 0.5526 0.01851 0.01053 -0.0502 0.6633 1.0000
2.500 0.5730 0.01863 0.01065 -0.0488 0.6535 1.0000
2.750 0.5926 0.01888 0.01092 -0.0474 0.6429 1.0000
3.000 0.6149 0.01890 0.01087 -0.0460 0.6350 1.0000
3.250 0.6337 0.01922 0.01125 -0.0446 0.6234 1.0000
3.500 0.6543 0.01940 0.01144 -0.0432 0.6134 1.0000
3.750 0.6765 0.01944 0.01143 -0.0418 0.6040 1.0000
4.000 0.6957 0.01966 0.01171 -0.0402 0.5919 1.0000
4.250 0.7167 0.01978 0.01184 -0.0387 0.5810 1.0000
4.500 0.7400 0.01975 0.01176 -0.0374 0.5714 1.0000
4.750 0.7592 0.02000 0.01208 -0.0358 0.5592 1.0000
5.000 0.7799 0.02017 0.01229 -0.0344 0.5481 1.0000
5.250 0.8043 0.02009 0.01215 -0.0331 0.5385 1.0000
5.500 0.8241 0.02022 0.01235 -0.0315 0.5255 1.0000
5.750 0.8441 0.02040 0.01259 -0.0300 0.5130 1.0000
6.000 0.8655 0.02056 0.01280 -0.0286 0.5018 1.0000
6.250 0.8899 0.02056 0.01275 -0.0275 0.4919 1.0000
6.500 0.9087 0.02088 0.01320 -0.0259 0.4793 1.0000
6.750 0.9288 0.02113 0.01354 -0.0243 0.4668 1.0000
7.000 0.9494 0.02123 0.01368 -0.0227 0.4528 1.0000
7.250 0.9694 0.02119 0.01365 -0.0209 0.4362 1.0000
7.500 0.9887 0.02111 0.01355 -0.0190 0.4177 1.0000
7.750 1.0076 0.02108 0.01347 -0.0171 0.3987 1.0000
8.000 1.0222 0.02130 0.01380 -0.0147 0.3779 1.0000
8.250 1.0368 0.02150 0.01401 -0.0123 0.3559 1.0000
8.500 1.0498 0.02183 0.01435 -0.0097 0.3330 1.0000
8.750 1.0605 0.02225 0.01476 -0.0069 0.3079 1.0000
9.000 1.0686 0.02284 0.01537 -0.0039 0.2802 1.0000
9.250 1.0732 0.02361 0.01607 -0.0004 0.2503 1.0000
9.500 1.0725 0.02464 0.01694 0.0036 0.2182 1.0000
9.750 1.0656 0.02603 0.01812 0.0082 0.1857 1.0000
10.000 1.0511 0.02765 0.01949 0.0137 0.1599 1.0000
10.250 1.0373 0.02962 0.02125 0.0183 0.1379 1.0000
10.500 1.0290 0.03171 0.02317 0.0217 0.1221 1.0000
10.750 1.0275 0.03371 0.02505 0.0242 0.1096 1.0000
11.000 1.0312 0.03552 0.02678 0.0263 0.1002 1.0000
11.250 1.0371 0.03717 0.02840 0.0279 0.0926 1.0000
11.500 1.0472 0.03878 0.03006 0.0294 0.0865 1.0000
11.750 1.0571 0.04033 0.03159 0.0308 0.0813 1.0000
12.000 1.0704 0.04198 0.03325 0.0320 0.0767 1.0000
12.250 1.0811 0.04368 0.03507 0.0333 0.0729 1.0000
12.500 1.0994 0.04524 0.03655 0.0342 0.0692 1.0000
12.750 1.1169 0.04747 0.03892 0.0352 0.0666 1.0000
13.000 1.1213 0.04975 0.04143 0.0364 0.0642 1.0000
13.250 1.1277 0.05212 0.04398 0.0374 0.0624 1.0000
13.500 1.1340 0.05446 0.04644 0.0382 0.0606 1.0000
13.750 1.1454 0.05721 0.04926 0.0389 0.0592 1.0000
14.000 1.1541 0.06126 0.05345 0.0395 0.0581 1.0000
14.250 1.1391 0.06482 0.05731 0.0401 0.0579 1.0000
14.500 1.1253 0.06867 0.06141 0.0403 0.0578 1.0000
14.750 1.1079 0.07309 0.06609 0.0399 0.0578 1.0000
15.000 1.0885 0.07794 0.07117 0.0390 0.0578 1.0000
15.250 1.0635 0.08346 0.07693 0.0372 0.0578 1.0000
15.500 1.0408 0.08943 0.08308 0.0350 0.0579 1.0000
15.750 1.0163 0.09605 0.08989 0.0322 0.0581 1.0000
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