NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Reynolds number: 500,000 Max Cl/Cd: 86.55 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12n1-il-500000.txt Download as CSV file: xf-rc12n1-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(N)1 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6428 0.08136 0.07934 -0.0145 1.0000 0.0230
-9.750 -0.6627 0.07383 0.07175 -0.0210 1.0000 0.0230
-9.500 -0.6791 0.06901 0.06684 -0.0230 1.0000 0.0231
-9.250 -0.6872 0.06554 0.06327 -0.0232 0.9372 0.0232
-9.000 -0.6949 0.06279 0.06028 -0.0214 0.8909 0.0234
-8.750 -0.6965 0.05988 0.05718 -0.0203 0.8719 0.0238
-8.500 -0.6941 0.05702 0.05414 -0.0194 0.8589 0.0243
-8.250 -0.6896 0.05395 0.05087 -0.0185 0.8488 0.0252
-8.000 -0.6794 0.05154 0.04791 -0.0162 0.8399 0.0282
-7.750 -0.6731 0.04850 0.04451 -0.0144 0.8324 0.0284
-7.500 -0.6802 0.04016 0.03581 -0.0126 0.8262 0.0294
-7.250 -0.6631 0.03799 0.03356 -0.0120 0.8200 0.0299
-7.000 -0.6454 0.03607 0.03152 -0.0113 0.8138 0.0306
-6.750 -0.6273 0.03418 0.02941 -0.0103 0.8085 0.0316
-6.500 -0.6159 0.02811 0.02244 -0.0066 0.8035 0.0294
-6.250 -0.5969 0.02220 0.01597 -0.0044 0.7987 0.0239
-6.000 -0.5731 0.02014 0.01359 -0.0035 0.7941 0.0238
-5.750 -0.5477 0.01886 0.01216 -0.0031 0.7891 0.0241
-5.500 -0.5219 0.01776 0.01096 -0.0027 0.7842 0.0245
-5.250 -0.4963 0.01683 0.00990 -0.0023 0.7799 0.0250
-5.000 -0.4702 0.01616 0.00916 -0.0019 0.7754 0.0260
-4.750 -0.4442 0.01545 0.00838 -0.0016 0.7705 0.0270
-4.500 -0.4186 0.01475 0.00760 -0.0011 0.7661 0.0277
-4.250 -0.3925 0.01431 0.00705 -0.0007 0.7622 0.0284
-4.000 -0.3705 0.01308 0.00580 0.0003 0.7575 0.0301
-3.750 -0.3452 0.01262 0.00533 0.0008 0.7530 0.0319
-3.500 -0.3194 0.01228 0.00492 0.0012 0.7490 0.0341
-3.250 -0.2923 0.01204 0.00465 0.0013 0.7448 0.0364
-3.000 -0.2677 0.01146 0.00406 0.0018 0.7402 0.0414
-2.750 -0.2408 0.01122 0.00378 0.0020 0.7360 0.0460
-2.500 -0.2148 0.01087 0.00342 0.0024 0.7322 0.0549
-2.250 -0.1881 0.01054 0.00313 0.0026 0.7277 0.0712
-2.000 -0.1697 0.00910 0.00264 0.0037 0.7233 0.3166
-1.750 -0.1545 0.00786 0.00249 0.0058 0.7194 0.6071
-1.500 -0.1291 0.00770 0.00247 0.0064 0.7153 0.6616
-1.250 -0.1028 0.00757 0.00242 0.0068 0.7107 0.6951
-1.000 -0.0763 0.00744 0.00234 0.0072 0.7064 0.7223
-0.750 -0.0498 0.00733 0.00227 0.0076 0.7026 0.7485
-0.500 -0.0233 0.00714 0.00224 0.0080 0.6977 0.7775
-0.250 0.0024 0.00696 0.00226 0.0087 0.6929 0.8226
0.000 0.0291 0.00691 0.00232 0.0093 0.6887 0.8714
0.250 0.0578 0.00692 0.00238 0.0094 0.6838 0.9023
0.500 0.0886 0.00695 0.00241 0.0089 0.6784 0.9217
0.750 0.1211 0.00701 0.00243 0.0081 0.6737 0.9367
1.000 0.1547 0.00708 0.00250 0.0070 0.6682 0.9484
1.250 0.1889 0.00716 0.00255 0.0057 0.6626 0.9578
1.500 0.2262 0.00726 0.00260 0.0038 0.6577 0.9635
1.750 0.2643 0.00734 0.00268 0.0015 0.6516 0.9688
2.000 0.3003 0.00740 0.00273 -0.0002 0.6456 0.9744
2.250 0.3397 0.00748 0.00278 -0.0028 0.6397 0.9780
2.500 0.3756 0.00753 0.00284 -0.0046 0.6328 0.9834
2.750 0.4141 0.00759 0.00287 -0.0069 0.6266 0.9868
3.000 0.4526 0.00760 0.00290 -0.0094 0.6181 0.9903
3.250 0.4890 0.00762 0.00291 -0.0113 0.6054 0.9944
3.500 0.5282 0.00760 0.00288 -0.0139 0.5904 0.9972
3.750 0.5663 0.00762 0.00288 -0.0163 0.5753 1.0000
4.000 0.5927 0.00765 0.00290 -0.0161 0.5622 1.0000
4.250 0.6191 0.00769 0.00294 -0.0160 0.5480 1.0000
4.500 0.6453 0.00775 0.00298 -0.0159 0.5293 1.0000
4.750 0.6712 0.00787 0.00304 -0.0157 0.5040 1.0000
5.000 0.6967 0.00805 0.00313 -0.0154 0.4713 1.0000
5.250 0.7213 0.00837 0.00330 -0.0151 0.4259 1.0000
5.500 0.7448 0.00885 0.00355 -0.0148 0.3727 1.0000
5.750 0.7674 0.00944 0.00388 -0.0143 0.3161 1.0000
6.000 0.7886 0.01012 0.00428 -0.0137 0.2544 1.0000
6.250 0.8084 0.01092 0.00476 -0.0128 0.1888 1.0000
6.500 0.8271 0.01173 0.00528 -0.0118 0.1344 1.0000
6.750 0.8461 0.01242 0.00578 -0.0107 0.1011 1.0000
7.000 0.8660 0.01296 0.00623 -0.0096 0.0813 1.0000
7.250 0.8857 0.01349 0.00671 -0.0085 0.0682 1.0000
7.500 0.9052 0.01402 0.00722 -0.0073 0.0589 1.0000
7.750 0.9233 0.01465 0.00781 -0.0059 0.0513 1.0000
8.000 0.9433 0.01509 0.00827 -0.0048 0.0463 1.0000
8.250 0.9597 0.01582 0.00901 -0.0032 0.0413 1.0000
8.500 0.9792 0.01626 0.00951 -0.0020 0.0383 1.0000
8.750 0.9964 0.01688 0.01013 -0.0006 0.0352 1.0000
9.000 1.0082 0.01789 0.01118 0.0017 0.0324 1.0000
9.250 1.0259 0.01842 0.01178 0.0030 0.0308 1.0000
9.500 1.0425 0.01902 0.01243 0.0045 0.0289 1.0000
9.750 1.0574 0.01974 0.01317 0.0060 0.0273 1.0000
10.000 1.0633 0.02113 0.01461 0.0087 0.0257 1.0000
10.250 1.0736 0.02206 0.01563 0.0108 0.0249 1.0000
10.500 1.0852 0.02288 0.01653 0.0127 0.0242 1.0000
10.750 1.0969 0.02380 0.01753 0.0142 0.0232 1.0000
11.000 1.1093 0.02476 0.01856 0.0154 0.0223 1.0000
11.250 1.1215 0.02580 0.01964 0.0164 0.0214 1.0000
11.500 1.1313 0.02711 0.02100 0.0175 0.0207 1.0000
11.750 1.1352 0.02918 0.02314 0.0192 0.0198 1.0000
12.000 1.1444 0.03077 0.02485 0.0203 0.0194 1.0000
12.250 1.1555 0.03210 0.02630 0.0211 0.0189 1.0000
12.500 1.1654 0.03356 0.02787 0.0218 0.0184 1.0000
12.750 1.1745 0.03509 0.02952 0.0225 0.0178 1.0000
13.000 1.1827 0.03670 0.03122 0.0231 0.0172 1.0000
13.250 1.1903 0.03837 0.03297 0.0235 0.0167 1.0000
13.500 1.1967 0.04017 0.03483 0.0238 0.0162 1.0000
13.750 1.2009 0.04226 0.03699 0.0243 0.0158 1.0000
14.000 1.1999 0.04508 0.03992 0.0251 0.0154 1.0000
14.250 1.1943 0.04855 0.04358 0.0260 0.0151 1.0000
14.500 1.1941 0.05124 0.04644 0.0258 0.0149 1.0000
14.750 1.1917 0.05427 0.04964 0.0256 0.0147 1.0000
15.000 1.1870 0.05769 0.05324 0.0252 0.0145 1.0000
15.250 1.1803 0.06146 0.05717 0.0245 0.0143 1.0000
15.500 1.1715 0.06569 0.06160 0.0234 0.0141 1.0000
15.750 1.1613 0.07039 0.06647 0.0218 0.0140 1.0000
16.000 1.1494 0.07557 0.07182 0.0198 0.0138 1.0000
16.250 1.1358 0.08132 0.07774 0.0173 0.0137 1.0000
16.500 1.1198 0.08779 0.08438 0.0142 0.0136 1.0000
16.750 1.1003 0.09519 0.09196 0.0104 0.0136 1.0000
17.000 1.0767 0.10388 0.10085 0.0057 0.0136 1.0000
17.250 1.0466 0.11446 0.11163 -0.0003 0.0138 1.0000
17.500 1.0073 0.12794 0.12531 -0.0081 0.0141 1.0000
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Polar data table (+)
Polar graphs
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