RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 500,000 Max Cl/Cd: 56.77 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf27-il-500000.txt Download as CSV file: xf-raf27-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 27 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7423 0.10017 0.09777 -0.0079 1.0000 0.0151
-12.750 -0.7784 0.08686 0.08445 -0.0154 1.0000 0.0145
-12.500 -0.8324 0.06977 0.06719 -0.0280 1.0000 0.0133
-12.250 -0.8474 0.06310 0.06039 -0.0335 1.0000 0.0136
-12.000 -0.8994 0.05226 0.04922 -0.0401 1.0000 0.0128
-11.750 -0.9595 0.04327 0.03970 -0.0404 1.0000 0.0123
-11.500 -0.9486 0.04304 0.03950 -0.0394 1.0000 0.0127
-11.250 -0.9644 0.04022 0.03646 -0.0362 1.0000 0.0128
-11.000 -0.9707 0.03857 0.03468 -0.0326 1.0000 0.0131
-10.750 -0.9772 0.03611 0.03197 -0.0290 1.0000 0.0133
-10.500 -0.9748 0.03427 0.02992 -0.0263 1.0000 0.0138
-10.250 -0.9731 0.03186 0.02722 -0.0232 1.0000 0.0141
-10.000 -0.9677 0.02956 0.02464 -0.0204 1.0000 0.0143
-9.750 -0.9581 0.02772 0.02253 -0.0180 1.0000 0.0147
-9.500 -0.9451 0.02631 0.02090 -0.0158 1.0000 0.0150
-9.250 -0.9351 0.02388 0.01818 -0.0134 1.0000 0.0155
-9.000 -0.9219 0.02198 0.01613 -0.0113 1.0000 0.0160
-8.750 -0.9047 0.02109 0.01519 -0.0097 1.0000 0.0166
-8.500 -0.8865 0.02034 0.01438 -0.0082 1.0000 0.0174
-8.250 -0.8677 0.01965 0.01361 -0.0067 1.0000 0.0183
-8.000 -0.8481 0.01906 0.01293 -0.0052 1.0000 0.0194
-7.750 -0.8280 0.01854 0.01230 -0.0038 1.0000 0.0201
-7.500 -0.8152 0.01676 0.01041 -0.0013 1.0000 0.0214
-7.250 -0.7972 0.01604 0.00968 0.0004 1.0000 0.0226
-7.000 -0.7780 0.01549 0.00908 0.0020 1.0000 0.0241
-6.750 -0.7578 0.01505 0.00859 0.0035 1.0000 0.0258
-6.500 -0.7386 0.01452 0.00798 0.0051 1.0000 0.0273
-6.250 -0.7236 0.01354 0.00697 0.0074 1.0000 0.0301
-6.000 -0.7043 0.01308 0.00648 0.0091 1.0000 0.0326
-5.750 -0.6843 0.01270 0.00605 0.0106 1.0000 0.0348
-5.500 -0.6669 0.01206 0.00538 0.0126 1.0000 0.0388
-5.250 -0.6474 0.01168 0.00498 0.0141 1.0000 0.0427
-5.000 -0.6273 0.01138 0.00463 0.0156 1.0000 0.0462
-4.750 -0.6085 0.01096 0.00426 0.0173 1.0000 0.0539
-4.500 -0.5893 0.01060 0.00396 0.0189 1.0000 0.0678
-4.250 -0.5614 0.01004 0.00359 0.0185 0.9983 0.1095
-4.000 -0.5275 0.00929 0.00330 0.0166 0.9949 0.2023
-3.750 -0.4935 0.00879 0.00309 0.0149 0.9910 0.2694
-3.500 -0.4587 0.00837 0.00290 0.0130 0.9869 0.3286
-3.250 -0.4222 0.00799 0.00275 0.0109 0.9837 0.3899
-3.000 -0.3903 0.00763 0.00260 0.0099 0.9780 0.4488
-2.750 -0.3553 0.00731 0.00247 0.0082 0.9734 0.5030
-2.500 -0.3186 0.00698 0.00236 0.0062 0.9703 0.5597
-2.250 -0.2889 0.00670 0.00225 0.0059 0.9626 0.6061
-2.000 -0.2530 0.00644 0.00216 0.0043 0.9581 0.6559
-1.750 -0.2194 0.00625 0.00207 0.0032 0.9512 0.6900
-1.500 -0.1840 0.00606 0.00196 0.0018 0.9436 0.7183
-1.250 -0.1511 0.00588 0.00187 0.0010 0.9320 0.7460
-1.000 -0.1174 0.00575 0.00178 0.0000 0.9189 0.7680
-0.750 -0.0852 0.00565 0.00171 -0.0006 0.9035 0.7877
-0.500 -0.0552 0.00559 0.00166 -0.0008 0.8854 0.8077
-0.250 -0.0271 0.00555 0.00163 -0.0005 0.8661 0.8268
0.000 0.0000 0.00554 0.00163 0.0000 0.8463 0.8463
0.250 0.0271 0.00555 0.00163 0.0005 0.8269 0.8663
0.500 0.0551 0.00559 0.00166 0.0008 0.8077 0.8855
0.750 0.0852 0.00565 0.00171 0.0006 0.7876 0.9035
1.000 0.1174 0.00575 0.00178 0.0000 0.7680 0.9190
1.250 0.1511 0.00588 0.00187 -0.0010 0.7463 0.9320
1.500 0.1839 0.00606 0.00196 -0.0018 0.7188 0.9436
1.750 0.2193 0.00625 0.00206 -0.0032 0.6887 0.9512
2.000 0.2528 0.00645 0.00216 -0.0043 0.6534 0.9582
2.250 0.2887 0.00670 0.00225 -0.0059 0.6048 0.9625
2.500 0.3186 0.00697 0.00236 -0.0062 0.5602 0.9703
2.750 0.3554 0.00730 0.00248 -0.0082 0.5044 0.9734
3.000 0.3904 0.00762 0.00260 -0.0099 0.4509 0.9780
3.250 0.4222 0.00798 0.00275 -0.0109 0.3910 0.9837
3.500 0.4587 0.00837 0.00290 -0.0130 0.3290 0.9869
3.750 0.4935 0.00880 0.00309 -0.0149 0.2684 0.9910
4.000 0.5274 0.00929 0.00331 -0.0166 0.2019 0.9949
4.250 0.5616 0.01002 0.00360 -0.0185 0.1113 0.9983
4.500 0.5894 0.01061 0.00396 -0.0190 0.0674 1.0000
4.750 0.6086 0.01096 0.00425 -0.0174 0.0538 1.0000
5.000 0.6273 0.01140 0.00465 -0.0156 0.0458 1.0000
5.250 0.6475 0.01168 0.00498 -0.0142 0.0426 1.0000
5.500 0.6671 0.01206 0.00538 -0.0126 0.0388 1.0000
5.750 0.6844 0.01270 0.00605 -0.0106 0.0349 1.0000
6.000 0.7045 0.01308 0.00649 -0.0091 0.0326 1.0000
6.250 0.7238 0.01353 0.00697 -0.0075 0.0301 1.0000
6.500 0.7387 0.01452 0.00798 -0.0051 0.0274 1.0000
6.750 0.7582 0.01502 0.00856 -0.0035 0.0257 1.0000
7.000 0.7779 0.01551 0.00911 -0.0020 0.0241 1.0000
7.250 0.7971 0.01607 0.00971 -0.0004 0.0227 1.0000
7.500 0.8153 0.01676 0.01042 0.0013 0.0214 1.0000
7.750 0.8278 0.01860 0.01235 0.0038 0.0201 1.0000
8.000 0.8481 0.01908 0.01295 0.0052 0.0195 1.0000
8.250 0.8676 0.01968 0.01364 0.0067 0.0184 1.0000
8.500 0.8868 0.02026 0.01430 0.0081 0.0173 1.0000
8.750 0.9050 0.02101 0.01511 0.0097 0.0166 1.0000
9.000 0.9218 0.02204 0.01620 0.0113 0.0161 1.0000
9.250 0.9340 0.02412 0.01843 0.0135 0.0153 1.0000
9.500 0.9452 0.02626 0.02085 0.0158 0.0149 1.0000
9.750 0.9585 0.02759 0.02241 0.0180 0.0146 1.0000
10.000 0.9681 0.02947 0.02454 0.0204 0.0143 1.0000
10.250 0.9736 0.03171 0.02707 0.0232 0.0139 1.0000
10.500 0.9774 0.03381 0.02943 0.0260 0.0136 1.0000
10.750 0.9765 0.03620 0.03207 0.0291 0.0133 1.0000
11.000 0.9828 0.03719 0.03316 0.0314 0.0127 1.0000
11.250 0.9640 0.04025 0.03650 0.0363 0.0128 1.0000
11.500 0.9697 0.04085 0.03712 0.0382 0.0124 1.0000
11.750 0.9587 0.04336 0.03978 0.0404 0.0122 1.0000
12.000 0.9269 0.04873 0.04549 0.0411 0.0124 1.0000
12.250 0.8574 0.06144 0.05869 0.0345 0.0130 1.0000
12.500 0.8125 0.07423 0.07171 0.0245 0.0139 1.0000
12.750 0.7762 0.08778 0.08538 0.0146 0.0145 1.0000
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