NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 500,000 Max Cl/Cd: 65.68 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc10b3-il-500000-n5.txt Download as CSV file: xf-rc10b3-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-10(B)3 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5901 0.08240 0.08008 -0.0212 1.0000 0.0117
-9.500 -0.6038 0.07480 0.07250 -0.0290 1.0000 0.0116
-9.250 -0.6225 0.06814 0.06579 -0.0329 1.0000 0.0115
-9.000 -0.6397 0.06173 0.05928 -0.0341 1.0000 0.0114
-8.750 -0.6557 0.05437 0.05173 -0.0341 1.0000 0.0114
-8.500 -0.7209 0.03119 0.02716 -0.0294 0.9811 0.0114
-8.250 -0.7104 0.02653 0.02186 -0.0279 0.9722 0.0116
-8.000 -0.6926 0.02412 0.01903 -0.0268 0.9641 0.0118
-7.750 -0.6718 0.02240 0.01700 -0.0259 0.9575 0.0119
-7.500 -0.6508 0.02111 0.01544 -0.0249 0.9502 0.0120
-7.250 -0.6304 0.01959 0.01367 -0.0237 0.9439 0.0122
-7.000 -0.6093 0.01834 0.01223 -0.0226 0.9370 0.0124
-6.750 -0.5869 0.01746 0.01122 -0.0216 0.9312 0.0126
-6.500 -0.5633 0.01680 0.01048 -0.0209 0.9250 0.0129
-6.250 -0.5394 0.01623 0.00983 -0.0202 0.9190 0.0133
-6.000 -0.5153 0.01564 0.00914 -0.0195 0.9135 0.0136
-5.750 -0.4909 0.01502 0.00842 -0.0188 0.9073 0.0140
-5.500 -0.4668 0.01440 0.00770 -0.0180 0.9017 0.0143
-5.250 -0.4421 0.01382 0.00705 -0.0174 0.8959 0.0146
-5.000 -0.4175 0.01331 0.00645 -0.0167 0.8900 0.0149
-4.750 -0.3928 0.01286 0.00592 -0.0160 0.8849 0.0153
-4.500 -0.3674 0.01245 0.00546 -0.0155 0.8788 0.0156
-4.250 -0.3430 0.01194 0.00491 -0.0148 0.8729 0.0161
-4.000 -0.3178 0.01156 0.00449 -0.0142 0.8676 0.0167
-3.750 -0.2920 0.01126 0.00416 -0.0138 0.8613 0.0174
-3.500 -0.2662 0.01099 0.00385 -0.0133 0.8557 0.0183
-3.250 -0.2400 0.01075 0.00358 -0.0129 0.8497 0.0194
-3.000 -0.2141 0.01047 0.00328 -0.0125 0.8433 0.0210
-2.750 -0.1880 0.01025 0.00303 -0.0120 0.8375 0.0230
-2.500 -0.1615 0.01003 0.00280 -0.0117 0.8304 0.0262
-2.250 -0.1355 0.00981 0.00259 -0.0112 0.8238 0.0333
-2.000 -0.1092 0.00960 0.00243 -0.0109 0.8164 0.0471
-1.750 -0.0832 0.00939 0.00228 -0.0105 0.8091 0.0677
-1.500 -0.0571 0.00917 0.00215 -0.0102 0.8012 0.0946
-1.250 -0.0314 0.00896 0.00203 -0.0097 0.7927 0.1302
-1.000 -0.0074 0.00852 0.00191 -0.0091 0.7830 0.2217
-0.750 0.0107 0.00760 0.00174 -0.0075 0.7740 0.4439
-0.500 0.0174 0.00630 0.00157 -0.0030 0.7649 0.7468
-0.250 0.0645 0.00618 0.00195 -0.0065 0.7565 0.9065
0.000 0.1029 0.00650 0.00222 -0.0083 0.7468 0.9367
0.250 0.1379 0.00679 0.00246 -0.0094 0.7348 0.9509
0.500 0.1793 0.00714 0.00273 -0.0120 0.7214 0.9630
0.750 0.2213 0.00736 0.00287 -0.0148 0.7074 0.9695
1.000 0.2459 0.00743 0.00287 -0.0141 0.6942 0.9734
1.250 0.2783 0.00746 0.00284 -0.0151 0.6793 0.9744
1.500 0.3100 0.00753 0.00281 -0.0160 0.6588 0.9754
1.750 0.3410 0.00761 0.00279 -0.0168 0.6337 0.9765
2.000 0.3715 0.00772 0.00279 -0.0175 0.6078 0.9778
2.250 0.4012 0.00784 0.00280 -0.0180 0.5815 0.9792
2.500 0.4304 0.00799 0.00284 -0.0184 0.5527 0.9807
2.750 0.4578 0.00823 0.00290 -0.0185 0.5088 0.9824
3.000 0.4836 0.00853 0.00300 -0.0183 0.4634 0.9843
3.250 0.5120 0.00882 0.00310 -0.0187 0.4202 0.9854
3.500 0.5408 0.00921 0.00324 -0.0193 0.3640 0.9861
3.750 0.5695 0.00959 0.00339 -0.0200 0.3126 0.9870
4.000 0.5984 0.00993 0.00354 -0.0206 0.2708 0.9880
4.250 0.6269 0.01025 0.00370 -0.0211 0.2365 0.9891
4.500 0.6546 0.01059 0.00390 -0.0214 0.2024 0.9901
5.000 0.7096 0.01128 0.00433 -0.0221 0.1449 0.9927
5.250 0.7362 0.01164 0.00459 -0.0222 0.1195 0.9938
5.500 0.7629 0.01204 0.00486 -0.0223 0.0950 0.9947
5.750 0.7908 0.01241 0.00513 -0.0228 0.0768 0.9955
6.000 0.8191 0.01277 0.00544 -0.0233 0.0634 0.9964
6.250 0.8471 0.01312 0.00574 -0.0237 0.0540 0.9973
6.500 0.8747 0.01345 0.00606 -0.0240 0.0479 0.9983
6.750 0.9017 0.01382 0.00641 -0.0243 0.0430 0.9991
7.000 0.9290 0.01415 0.00678 -0.0245 0.0401 0.9999
7.250 0.9510 0.01448 0.00713 -0.0236 0.0375 1.0000
7.500 0.9712 0.01488 0.00753 -0.0224 0.0349 1.0000
7.750 0.9911 0.01528 0.00795 -0.0211 0.0332 1.0000
8.000 1.0111 0.01563 0.00837 -0.0198 0.0320 1.0000
8.250 1.0305 0.01601 0.00880 -0.0184 0.0306 1.0000
8.500 1.0493 0.01643 0.00924 -0.0170 0.0293 1.0000
8.750 1.0671 0.01691 0.00974 -0.0153 0.0280 1.0000
9.000 1.0831 0.01749 0.01037 -0.0134 0.0267 1.0000
9.250 1.1008 0.01790 0.01084 -0.0118 0.0259 1.0000
9.500 1.1174 0.01837 0.01137 -0.0100 0.0251 1.0000
9.750 1.1332 0.01886 0.01192 -0.0080 0.0243 1.0000
10.000 1.1483 0.01936 0.01248 -0.0060 0.0236 1.0000
10.250 1.1624 0.01989 0.01306 -0.0038 0.0228 1.0000
10.500 1.1749 0.02047 0.01368 -0.0014 0.0221 1.0000
10.750 1.1835 0.02127 0.01452 0.0016 0.0212 1.0000
11.000 1.1952 0.02182 0.01514 0.0042 0.0208 1.0000
11.250 1.2039 0.02238 0.01579 0.0072 0.0204 1.0000
11.500 1.2090 0.02296 0.01646 0.0109 0.0199 1.0000
11.750 1.2152 0.02360 0.01716 0.0142 0.0194 1.0000
12.000 1.2226 0.02428 0.01792 0.0170 0.0189 1.0000
12.250 1.2313 0.02500 0.01870 0.0195 0.0183 1.0000
12.500 1.2403 0.02580 0.01957 0.0217 0.0178 1.0000
12.750 1.2483 0.02676 0.02059 0.0238 0.0174 1.0000
13.000 1.2538 0.02799 0.02188 0.0259 0.0169 1.0000
13.250 1.2596 0.02931 0.02330 0.0277 0.0166 1.0000
13.500 1.2680 0.03049 0.02461 0.0292 0.0162 1.0000
13.750 1.2758 0.03179 0.02602 0.0305 0.0158 1.0000
14.000 1.2829 0.03320 0.02754 0.0317 0.0154 1.0000
14.250 1.2894 0.03472 0.02916 0.0327 0.0150 1.0000
14.500 1.2953 0.03637 0.03091 0.0336 0.0146 1.0000
14.750 1.3000 0.03818 0.03282 0.0343 0.0143 1.0000
15.000 1.3035 0.04021 0.03495 0.0348 0.0140 1.0000
15.250 1.3051 0.04252 0.03735 0.0351 0.0137 1.0000
15.500 1.3044 0.04519 0.04014 0.0352 0.0135 1.0000
15.750 1.3005 0.04836 0.04342 0.0349 0.0132 1.0000
16.000 1.2944 0.05195 0.04713 0.0343 0.0130 1.0000
16.250 1.2904 0.05549 0.05082 0.0335 0.0129 1.0000
16.500 1.2849 0.05944 0.05492 0.0322 0.0127 1.0000
16.750 1.2774 0.06383 0.05947 0.0306 0.0126 1.0000
17.000 1.2682 0.06872 0.06451 0.0286 0.0124 1.0000
17.250 1.2569 0.07415 0.07009 0.0261 0.0123 1.0000
17.500 1.2435 0.08008 0.07617 0.0233 0.0121 1.0000
17.750 1.2278 0.08659 0.08283 0.0201 0.0120 1.0000
18.000 1.2100 0.09365 0.09004 0.0166 0.0120 1.0000
18.250 1.1900 0.10122 0.09775 0.0128 0.0119 1.0000
18.500 1.1684 0.10929 0.10596 0.0087 0.0119 1.0000
18.750 1.1451 0.11789 0.11471 0.0042 0.0118 1.0000
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Polar data table (+)
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