NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Reynolds number: 200,000 Max Cl/Cd: 49.27 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc08b3-il-200000-n5.txt Download as CSV file: xf-rc08b3-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-08(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6014 0.09736 0.09376 -0.0036 1.0000 0.0231
-9.250 -0.6016 0.09312 0.08954 -0.0054 1.0000 0.0223
-9.000 -0.6041 0.08820 0.08465 -0.0085 1.0000 0.0216
-8.750 -0.6096 0.08255 0.07904 -0.0133 1.0000 0.0211
-8.500 -0.6185 0.07680 0.07327 -0.0176 1.0000 0.0206
-8.250 -0.6250 0.07078 0.06718 -0.0208 1.0000 0.0200
-8.000 -0.6283 0.06480 0.06108 -0.0229 1.0000 0.0197
-7.750 -0.6258 0.06021 0.05636 -0.0237 1.0000 0.0201
-7.500 -0.6216 0.05566 0.05164 -0.0238 1.0000 0.0206
-7.250 -0.6167 0.05090 0.04665 -0.0233 1.0000 0.0209
-7.000 -0.6120 0.04579 0.04124 -0.0219 1.0000 0.0204
-6.750 -0.6070 0.04063 0.03570 -0.0197 1.0000 0.0199
-6.500 -0.6013 0.03585 0.03048 -0.0169 1.0000 0.0195
-6.250 -0.5934 0.03200 0.02619 -0.0138 1.0000 0.0194
-6.000 -0.5825 0.02906 0.02285 -0.0110 1.0000 0.0195
-5.750 -0.5694 0.02671 0.02014 -0.0084 1.0000 0.0197
-5.500 -0.5545 0.02475 0.01784 -0.0060 1.0000 0.0200
-5.250 -0.5381 0.02307 0.01586 -0.0039 1.0000 0.0204
-5.000 -0.5160 0.02171 0.01424 -0.0030 0.9989 0.0212
-4.750 -0.4842 0.02043 0.01267 -0.0039 0.9956 0.0226
-4.500 -0.4525 0.01905 0.01104 -0.0048 0.9924 0.0231
-4.250 -0.4209 0.01781 0.00963 -0.0056 0.9889 0.0235
-4.000 -0.3882 0.01677 0.00846 -0.0067 0.9858 0.0239
-3.750 -0.3570 0.01575 0.00735 -0.0075 0.9822 0.0246
-3.500 -0.3263 0.01483 0.00640 -0.0084 0.9779 0.0259
-3.250 -0.2933 0.01421 0.00575 -0.0097 0.9744 0.0275
-3.000 -0.2618 0.01373 0.00524 -0.0106 0.9698 0.0300
-2.750 -0.2308 0.01331 0.00476 -0.0113 0.9645 0.0339
-2.500 -0.1980 0.01282 0.00428 -0.0125 0.9604 0.0406
-2.250 -0.1686 0.01239 0.00389 -0.0128 0.9543 0.0573
-2.000 -0.1386 0.01194 0.00361 -0.0135 0.9485 0.0985
-1.750 -0.1105 0.01123 0.00337 -0.0140 0.9431 0.2119
-1.500 -0.1003 0.00927 0.00318 -0.0109 0.9341 0.6316
-1.250 -0.0402 0.00906 0.00381 -0.0160 0.9374 0.9150
-1.000 0.0028 0.00930 0.00397 -0.0185 0.9336 0.9500
-0.750 0.0703 0.00959 0.00417 -0.0264 0.9349 0.9831
-0.500 0.1302 0.00951 0.00401 -0.0333 0.9320 0.9966
-0.250 0.1653 0.00941 0.00385 -0.0348 0.9202 1.0000
0.000 0.1895 0.00934 0.00373 -0.0340 0.9054 1.0000
0.250 0.2132 0.00928 0.00362 -0.0330 0.8907 1.0000
0.500 0.2369 0.00923 0.00353 -0.0320 0.8763 1.0000
0.750 0.2605 0.00918 0.00344 -0.0310 0.8611 1.0000
1.000 0.2843 0.00915 0.00336 -0.0300 0.8454 1.0000
1.250 0.3084 0.00912 0.00331 -0.0291 0.8290 1.0000
1.500 0.3328 0.00911 0.00327 -0.0282 0.8114 1.0000
1.750 0.3570 0.00911 0.00323 -0.0273 0.7905 1.0000
2.000 0.3814 0.00912 0.00320 -0.0264 0.7660 1.0000
2.250 0.4059 0.00915 0.00318 -0.0255 0.7392 1.0000
2.500 0.4302 0.00923 0.00316 -0.0245 0.7045 1.0000
2.750 0.4540 0.00938 0.00314 -0.0235 0.6557 1.0000
3.000 0.4769 0.00968 0.00316 -0.0223 0.5817 1.0000
3.250 0.4988 0.01017 0.00324 -0.0212 0.4901 1.0000
3.500 0.5206 0.01077 0.00343 -0.0202 0.4004 1.0000
3.750 0.5425 0.01138 0.00368 -0.0194 0.3198 1.0000
4.000 0.5643 0.01200 0.00398 -0.0186 0.2466 1.0000
4.250 0.5857 0.01267 0.00434 -0.0178 0.1760 1.0000
4.500 0.6071 0.01332 0.00472 -0.0170 0.1202 1.0000
4.750 0.6286 0.01394 0.00514 -0.0161 0.0828 1.0000
5.000 0.6503 0.01449 0.00561 -0.0151 0.0639 1.0000
5.250 0.6721 0.01501 0.00611 -0.0141 0.0532 1.0000
5.500 0.6936 0.01553 0.00669 -0.0130 0.0458 1.0000
5.750 0.7147 0.01610 0.00727 -0.0119 0.0405 1.0000
6.000 0.7349 0.01678 0.00801 -0.0106 0.0374 1.0000
6.250 0.7554 0.01741 0.00873 -0.0094 0.0350 1.0000
6.500 0.7754 0.01810 0.00949 -0.0080 0.0329 1.0000
6.750 0.7950 0.01883 0.01031 -0.0067 0.0310 1.0000
7.000 0.8128 0.01987 0.01136 -0.0051 0.0288 1.0000
7.250 0.8322 0.02073 0.01233 -0.0037 0.0274 1.0000
7.500 0.8517 0.02167 0.01340 -0.0023 0.0263 1.0000
7.750 0.8710 0.02272 0.01458 -0.0009 0.0251 1.0000
8.000 0.8900 0.02382 0.01582 0.0005 0.0240 1.0000
8.250 0.9088 0.02475 0.01688 0.0018 0.0227 1.0000
8.500 0.9265 0.02573 0.01791 0.0031 0.0214 1.0000
8.750 0.9424 0.02754 0.01990 0.0047 0.0203 1.0000
9.000 0.9589 0.02908 0.02174 0.0064 0.0196 1.0000
9.250 0.9737 0.03089 0.02386 0.0082 0.0187 1.0000
9.500 0.9874 0.03255 0.02579 0.0100 0.0177 1.0000
9.750 1.0008 0.03384 0.02731 0.0116 0.0167 1.0000
10.000 1.0140 0.03488 0.02846 0.0131 0.0159 1.0000
10.250 1.0240 0.03649 0.03020 0.0149 0.0153 1.0000
10.500 1.0256 0.03943 0.03344 0.0174 0.0148 1.0000
10.750 1.0230 0.04247 0.03692 0.0202 0.0145 1.0000
11.000 1.0127 0.04586 0.04070 0.0235 0.0143 1.0000
11.250 0.9957 0.04932 0.04447 0.0267 0.0141 1.0000
11.500 0.9762 0.05336 0.04880 0.0284 0.0140 1.0000
11.750 0.9548 0.05820 0.05390 0.0281 0.0140 1.0000
12.000 0.9325 0.06406 0.05998 0.0257 0.0140 1.0000
12.250 0.9094 0.07145 0.06755 0.0207 0.0142 1.0000
12.500 0.8855 0.08111 0.07736 0.0131 0.0144 1.0000
12.750 0.8577 0.09376 0.09010 0.0041 0.0147 1.0000
13.000 0.8188 0.11018 0.10651 -0.0046 0.0150 1.0000
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Polar data table (+)
Polar graphs
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