RAF 69 AIRFOIL (raf69-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 69 AIRFOIL (raf69-il) Reynolds number: 100,000 Max Cl/Cd: 40.28 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf69-il-100000.txt Download as CSV file: xf-raf69-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 69 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8040 0.06448 0.05792 -0.0801 1.0000 0.1563
-14.000 -0.8850 0.05597 0.04911 -0.0800 1.0000 0.1559
-13.750 -0.9376 0.05139 0.04428 -0.0770 1.0000 0.1565
-13.500 -0.9797 0.04843 0.04111 -0.0724 1.0000 0.1573
-13.250 -0.9572 0.04769 0.04052 -0.0716 1.0000 0.1612
-13.000 -0.9583 0.04677 0.03963 -0.0688 1.0000 0.1642
-12.750 -0.9832 0.04543 0.03823 -0.0634 1.0000 0.1661
-12.500 -1.0162 0.04444 0.03715 -0.0561 1.0000 0.1673
-12.250 -1.0530 0.04380 0.03643 -0.0476 1.0000 0.1682
-12.000 -1.0855 0.04299 0.03549 -0.0397 1.0000 0.1696
-11.750 -1.1148 0.04199 0.03428 -0.0324 1.0000 0.1712
-11.500 -1.1099 0.04118 0.03356 -0.0296 1.0000 0.1747
-11.250 -1.1069 0.04076 0.03322 -0.0265 1.0000 0.1784
-11.000 -1.1160 0.04000 0.03234 -0.0218 1.0000 0.1819
-10.750 -1.1305 0.03897 0.03105 -0.0164 1.0000 0.1855
-10.500 -1.1156 0.03819 0.03035 -0.0152 0.9987 0.1905
-10.250 -1.0845 0.03756 0.02964 -0.0173 0.9922 0.1987
-10.000 -1.0576 0.03661 0.02863 -0.0185 0.9850 0.2062
-9.750 -1.0249 0.03607 0.02801 -0.0206 0.9787 0.2152
-9.500 -1.0027 0.03530 0.02722 -0.0207 0.9712 0.2228
-9.250 -0.9721 0.03482 0.02664 -0.0222 0.9648 0.2324
-9.000 -0.9490 0.03418 0.02602 -0.0222 0.9572 0.2402
-8.750 -0.9212 0.03374 0.02548 -0.0231 0.9502 0.2499
-8.500 -0.8936 0.03325 0.02502 -0.0238 0.9441 0.2583
-8.250 -0.8741 0.03287 0.02454 -0.0230 0.9360 0.2672
-8.000 -0.8355 0.03241 0.02413 -0.0255 0.9309 0.2773
-7.750 -0.8246 0.03212 0.02373 -0.0232 0.9221 0.2852
-7.500 -0.7946 0.03170 0.02333 -0.0241 0.9158 0.2946
-7.250 -0.7581 0.03134 0.02280 -0.0261 0.9112 0.3065
-7.000 -0.7498 0.03111 0.02269 -0.0231 0.9013 0.3129
-6.750 -0.7193 0.03080 0.02227 -0.0240 0.8954 0.3239
-6.500 -0.6730 0.03043 0.02201 -0.0275 0.8918 0.3353
-6.250 -0.6768 0.03032 0.02179 -0.0223 0.8803 0.3423
-6.000 -0.6385 0.02996 0.02151 -0.0244 0.8752 0.3531
-5.750 -0.6195 0.02977 0.02115 -0.0231 0.8680 0.3638
-5.500 -0.5985 0.02960 0.02114 -0.0221 0.8596 0.3726
-5.250 -0.5618 0.02920 0.02066 -0.0238 0.8545 0.3860
-5.000 -0.5416 0.02916 0.02071 -0.0226 0.8467 0.3963
-4.750 -0.5229 0.02898 0.02051 -0.0212 0.8385 0.4074
-4.500 -0.4836 0.02863 0.02011 -0.0231 0.8338 0.4234
-4.250 -0.4697 0.02871 0.02034 -0.0208 0.8249 0.4337
-4.000 -0.4463 0.02855 0.02019 -0.0201 0.8173 0.4477
-3.750 -0.4033 0.02817 0.01984 -0.0223 0.8133 0.4659
-3.500 -0.3999 0.02844 0.02016 -0.0184 0.8029 0.4779
-3.250 -0.3701 0.02827 0.02008 -0.0185 0.7962 0.4946
-3.000 -0.3232 0.02786 0.01973 -0.0212 0.7928 0.5156
-2.750 -0.3271 0.02828 0.02019 -0.0161 0.7809 0.5279
-2.500 -0.2929 0.02807 0.02004 -0.0167 0.7752 0.5475
-2.250 -0.2418 0.02765 0.01971 -0.0198 0.7723 0.5698
-2.000 -0.2551 0.02825 0.02029 -0.0133 0.7588 0.5836
-1.750 -0.2141 0.02798 0.02010 -0.0147 0.7544 0.6043
-1.500 -0.1605 0.02759 0.01979 -0.0180 0.7518 0.6257
-1.250 -0.1735 0.02839 0.02069 -0.0114 0.7378 0.6372
-1.000 -0.1263 0.02808 0.02044 -0.0136 0.7340 0.6572
-0.750 -0.0731 0.02771 0.02010 -0.0167 0.7315 0.6769
-0.500 -0.0935 0.02861 0.02104 -0.0091 0.7168 0.6898
-0.250 -0.0437 0.02824 0.02069 -0.0115 0.7135 0.7090
0.000 0.0074 0.02776 0.02020 -0.0141 0.7110 0.7278
0.250 -0.0111 0.02884 0.02137 -0.0068 0.6962 0.7401
0.500 0.0411 0.02838 0.02093 -0.0094 0.6932 0.7576
0.750 0.0950 0.02782 0.02036 -0.0123 0.6907 0.7747
1.000 0.0686 0.02884 0.02144 -0.0039 0.6757 0.7910
1.250 0.1197 0.02826 0.02084 -0.0063 0.6729 0.8088
1.500 0.1890 0.02773 0.02030 -0.0116 0.6705 0.8215
1.750 0.1686 0.02879 0.02146 -0.0042 0.6560 0.8381
2.000 0.2296 0.02818 0.02081 -0.0084 0.6530 0.8526
2.250 0.3157 0.02761 0.02017 -0.0168 0.6504 0.8612
2.500 0.3119 0.02863 0.02129 -0.0122 0.6368 0.8771
2.750 0.3918 0.02800 0.02057 -0.0198 0.6329 0.8858
3.000 0.4291 0.02854 0.02116 -0.0218 0.6226 0.8961
3.250 0.5061 0.02810 0.02066 -0.0296 0.6156 0.9023
3.500 0.5703 0.02753 0.01997 -0.0351 0.6099 0.9112
3.750 0.6154 0.02794 0.02045 -0.0387 0.5979 0.9192
4.000 0.6730 0.02723 0.01960 -0.0432 0.5921 0.9290
4.250 0.7121 0.02772 0.02019 -0.0461 0.5797 0.9379
4.500 0.7676 0.02707 0.01940 -0.0505 0.5732 0.9473
4.750 0.8042 0.02746 0.01990 -0.0530 0.5610 0.9573
5.000 0.8637 0.02678 0.01905 -0.0583 0.5536 0.9651
5.250 0.8948 0.02714 0.01954 -0.0600 0.5412 0.9764
5.500 0.9508 0.02666 0.01897 -0.0652 0.5319 0.9838
5.750 0.9920 0.02658 0.01892 -0.0684 0.5200 0.9935
6.000 1.0304 0.02648 0.01881 -0.0711 0.5094 1.0000
6.250 1.0420 0.02645 0.01875 -0.0687 0.5007 1.0000
6.500 1.0505 0.02660 0.01887 -0.0658 0.4922 1.0000
6.750 1.0550 0.02675 0.01903 -0.0623 0.4831 1.0000
7.000 1.0684 0.02676 0.01897 -0.0601 0.4747 1.0000
7.250 1.0638 0.02707 0.01933 -0.0551 0.4657 1.0000
7.500 1.0838 0.02697 0.01910 -0.0537 0.4573 1.0000
7.750 1.0662 0.02747 0.01970 -0.0467 0.4489 1.0000
8.000 1.0972 0.02724 0.01926 -0.0469 0.4400 1.0000
8.250 1.0681 0.02791 0.02007 -0.0380 0.4324 1.0000
8.500 1.0963 0.02779 0.01977 -0.0378 0.4231 1.0000
8.750 1.0791 0.02848 0.02055 -0.0307 0.4152 1.0000
9.000 1.1000 0.02856 0.02051 -0.0293 0.4058 1.0000
9.250 1.0953 0.02921 0.02119 -0.0242 0.3975 1.0000
9.500 1.1099 0.02947 0.02139 -0.0220 0.3884 1.0000
9.750 1.1129 0.03007 0.02198 -0.0181 0.3801 1.0000
10.000 1.1144 0.03053 0.02243 -0.0140 0.3717 1.0000
10.250 1.1294 0.03097 0.02279 -0.0119 0.3632 1.0000
10.500 1.1195 0.03172 0.02361 -0.0064 0.3553 1.0000
10.750 1.1487 0.03195 0.02371 -0.0065 0.3465 1.0000
11.000 1.1299 0.03307 0.02495 -0.0002 0.3392 1.0000
11.250 1.1716 0.03304 0.02471 -0.0019 0.3300 1.0000
11.500 1.1448 0.03456 0.02644 0.0049 0.3234 1.0000
11.750 1.1777 0.03461 0.02633 0.0044 0.3147 1.0000
12.000 1.1637 0.03613 0.02799 0.0090 0.3080 1.0000
12.250 1.1711 0.03698 0.02883 0.0112 0.3003 1.0000
12.500 1.1897 0.03769 0.02950 0.0121 0.2930 1.0000
12.750 1.1736 0.03956 0.03152 0.0161 0.2867 1.0000
13.000 1.2252 0.03913 0.03082 0.0140 0.2783 1.0000
13.250 1.1920 0.04180 0.03377 0.0192 0.2735 1.0000
13.500 1.1930 0.04325 0.03528 0.0212 0.2672 1.0000
13.750 1.2316 0.04335 0.03523 0.0204 0.2604 1.0000
14.000 1.1972 0.04667 0.03881 0.0245 0.2561 1.0000
14.250 1.1931 0.04869 0.04092 0.0262 0.2509 1.0000
14.500 1.2476 0.04786 0.03987 0.0249 0.2443 1.0000
14.750 1.1995 0.05246 0.04479 0.0286 0.2411 1.0000
15.000 1.1525 0.05794 0.05053 0.0308 0.2374 1.0000
15.250 1.1699 0.05882 0.05139 0.0313 0.2327 1.0000
15.500 1.2094 0.05843 0.05092 0.0313 0.2276 1.0000
15.750 0.5451 0.16247 0.15567 -0.0056 0.2660 1.0000
16.000 0.5768 0.16533 0.15858 -0.0051 0.2630 1.0000
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