NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.54 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc10b3-il-1000000-n5.txt Download as CSV file: xf-rc10b3-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.9093 0.03644 0.03382 -0.0324 1.0000 0.0084
-10.500 -0.9253 0.03034 0.02715 -0.0285 1.0000 0.0085
-10.250 -0.9150 0.02736 0.02382 -0.0272 0.9887 0.0086
-10.000 -0.8975 0.02521 0.02139 -0.0266 0.9769 0.0087
-9.750 -0.8790 0.02361 0.01956 -0.0256 0.9669 0.0088
-9.500 -0.8608 0.02230 0.01805 -0.0244 0.9579 0.0089
-9.250 -0.8420 0.02123 0.01679 -0.0231 0.9495 0.0090
-9.000 -0.8224 0.02026 0.01565 -0.0218 0.9426 0.0090
-8.750 -0.8015 0.01940 0.01464 -0.0207 0.9358 0.0091
-8.500 -0.7832 0.01803 0.01305 -0.0192 0.9295 0.0092
-8.250 -0.7627 0.01688 0.01172 -0.0181 0.9232 0.0093
-8.000 -0.7407 0.01607 0.01078 -0.0171 0.9172 0.0095
-7.750 -0.7174 0.01540 0.01001 -0.0164 0.9117 0.0096
-7.500 -0.6935 0.01483 0.00935 -0.0158 0.9056 0.0097
-7.250 -0.6694 0.01431 0.00875 -0.0151 0.9002 0.0099
-7.000 -0.6446 0.01381 0.00819 -0.0146 0.8945 0.0100
-6.750 -0.6198 0.01334 0.00764 -0.0140 0.8887 0.0101
-6.500 -0.5949 0.01290 0.00712 -0.0135 0.8834 0.0103
-6.250 -0.5695 0.01247 0.00663 -0.0130 0.8776 0.0105
-6.000 -0.5442 0.01206 0.00616 -0.0125 0.8720 0.0107
-5.750 -0.5185 0.01171 0.00574 -0.0121 0.8667 0.0110
-5.500 -0.4925 0.01138 0.00536 -0.0118 0.8610 0.0113
-5.250 -0.4667 0.01107 0.00499 -0.0114 0.8554 0.0116
-5.000 -0.4405 0.01075 0.00463 -0.0110 0.8500 0.0118
-4.750 -0.4143 0.01047 0.00430 -0.0107 0.8441 0.0120
-4.250 -0.3623 0.00981 0.00355 -0.0099 0.8328 0.0126
-4.000 -0.3360 0.00955 0.00326 -0.0096 0.8267 0.0131
-3.750 -0.3094 0.00934 0.00302 -0.0093 0.8209 0.0135
-3.500 -0.2825 0.00914 0.00280 -0.0091 0.8144 0.0140
-3.250 -0.2558 0.00897 0.00259 -0.0088 0.8078 0.0146
-3.000 -0.2287 0.00880 0.00240 -0.0086 0.8006 0.0152
-2.750 -0.2018 0.00865 0.00221 -0.0084 0.7932 0.0159
-2.500 -0.1748 0.00848 0.00204 -0.0082 0.7858 0.0177
-2.250 -0.1478 0.00836 0.00189 -0.0080 0.7778 0.0198
-2.000 -0.1208 0.00821 0.00176 -0.0078 0.7684 0.0248
-1.750 -0.0941 0.00806 0.00163 -0.0075 0.7585 0.0356
-1.500 -0.0673 0.00793 0.00153 -0.0073 0.7485 0.0494
-1.250 -0.0403 0.00779 0.00144 -0.0071 0.7394 0.0662
-0.750 0.0129 0.00749 0.00128 -0.0066 0.7195 0.1235
-0.500 0.0383 0.00723 0.00121 -0.0062 0.7079 0.1921
-0.250 0.0614 0.00678 0.00113 -0.0054 0.6946 0.3203
0.000 0.0812 0.00611 0.00104 -0.0040 0.6810 0.5097
0.250 0.0914 0.00511 0.00091 -0.0003 0.6680 0.7704
0.500 0.1176 0.00484 0.00110 0.0005 0.6544 0.9126
0.750 0.1518 0.00506 0.00131 -0.0006 0.6394 0.9427
1.000 0.1820 0.00530 0.00147 -0.0009 0.6193 0.9545
1.250 0.2149 0.00564 0.00170 -0.0018 0.5926 0.9636
1.500 0.2525 0.00591 0.00184 -0.0040 0.5598 0.9661
1.750 0.2822 0.00607 0.00188 -0.0045 0.5315 0.9675
2.000 0.3107 0.00622 0.00192 -0.0047 0.5066 0.9692
2.250 0.3333 0.00639 0.00198 -0.0037 0.4782 0.9724
2.500 0.3594 0.00664 0.00206 -0.0034 0.4361 0.9740
3.000 0.4200 0.00714 0.00224 -0.0050 0.3617 0.9750
3.250 0.4494 0.00747 0.00236 -0.0057 0.3150 0.9757
3.500 0.4782 0.00781 0.00250 -0.0062 0.2673 0.9764
3.750 0.5073 0.00810 0.00264 -0.0068 0.2338 0.9772
4.000 0.5361 0.00837 0.00278 -0.0072 0.2040 0.9781
4.250 0.5642 0.00865 0.00293 -0.0076 0.1763 0.9791
4.500 0.5917 0.00892 0.00309 -0.0078 0.1532 0.9803
4.750 0.6187 0.00917 0.00326 -0.0078 0.1330 0.9817
5.000 0.6430 0.00948 0.00346 -0.0073 0.1105 0.9836
5.250 0.6671 0.00979 0.00366 -0.0068 0.0899 0.9851
5.500 0.6961 0.01008 0.00387 -0.0074 0.0745 0.9855
5.750 0.7252 0.01036 0.00409 -0.0079 0.0613 0.9861
6.000 0.7541 0.01065 0.00432 -0.0085 0.0510 0.9866
6.250 0.7830 0.01091 0.00455 -0.0090 0.0451 0.9873
6.500 0.8113 0.01115 0.00478 -0.0095 0.0407 0.9880
6.750 0.8392 0.01142 0.00503 -0.0098 0.0370 0.9887
7.000 0.8666 0.01170 0.00529 -0.0100 0.0335 0.9895
7.250 0.8942 0.01194 0.00556 -0.0103 0.0319 0.9904
7.500 0.9214 0.01222 0.00583 -0.0105 0.0301 0.9914
7.750 0.9477 0.01253 0.00614 -0.0105 0.0282 0.9924
8.000 0.9730 0.01286 0.00649 -0.0103 0.0266 0.9934
8.250 0.9981 0.01313 0.00679 -0.0101 0.0258 0.9943
8.500 1.0253 0.01342 0.00710 -0.0103 0.0246 0.9948
8.750 1.0524 0.01375 0.00745 -0.0106 0.0235 0.9953
9.000 1.0791 0.01413 0.00784 -0.0109 0.0223 0.9959
9.250 1.1053 0.01458 0.00831 -0.0111 0.0211 0.9966
9.500 1.1319 0.01492 0.00869 -0.0113 0.0207 0.9973
9.750 1.1578 0.01527 0.00908 -0.0114 0.0200 0.9980
10.000 1.1831 0.01565 0.00950 -0.0114 0.0191 0.9987
10.250 1.2079 0.01607 0.00995 -0.0113 0.0184 0.9993
10.500 1.2321 0.01654 0.01043 -0.0112 0.0176 0.9999
10.750 1.2490 0.01708 0.01100 -0.0096 0.0167 1.0000
11.000 1.2652 0.01746 0.01143 -0.0077 0.0164 1.0000
11.250 1.2804 0.01787 0.01190 -0.0057 0.0160 1.0000
11.500 1.2947 0.01829 0.01237 -0.0035 0.0156 1.0000
11.750 1.3080 0.01873 0.01285 -0.0011 0.0151 1.0000
12.000 1.3203 0.01918 0.01334 0.0013 0.0146 1.0000
12.250 1.3308 0.01967 0.01386 0.0041 0.0142 1.0000
12.500 1.3350 0.02014 0.01438 0.0081 0.0138 1.0000
12.750 1.3387 0.02071 0.01499 0.0120 0.0134 1.0000
13.000 1.3439 0.02139 0.01573 0.0154 0.0130 1.0000
13.250 1.3528 0.02201 0.01643 0.0179 0.0128 1.0000
13.500 1.3625 0.02271 0.01719 0.0202 0.0126 1.0000
13.750 1.3726 0.02348 0.01803 0.0221 0.0123 1.0000
14.000 1.3831 0.02432 0.01894 0.0239 0.0120 1.0000
14.250 1.3935 0.02522 0.01990 0.0255 0.0116 1.0000
14.500 1.4036 0.02620 0.02095 0.0269 0.0113 1.0000
14.750 1.4129 0.02729 0.02210 0.0283 0.0109 1.0000
15.000 1.4210 0.02853 0.02340 0.0296 0.0106 1.0000
15.250 1.4271 0.02999 0.02494 0.0308 0.0102 1.0000
15.500 1.4322 0.03159 0.02663 0.0319 0.0100 1.0000
15.750 1.4387 0.03315 0.02828 0.0328 0.0098 1.0000
16.000 1.4440 0.03487 0.03009 0.0336 0.0097 1.0000
16.250 1.4481 0.03677 0.03209 0.0342 0.0095 1.0000
16.500 1.4511 0.03887 0.03429 0.0346 0.0093 1.0000
16.750 1.4527 0.04119 0.03672 0.0348 0.0091 1.0000
17.000 1.4528 0.04376 0.03939 0.0348 0.0089 1.0000
17.250 1.4515 0.04664 0.04237 0.0346 0.0087 1.0000
17.500 1.4484 0.04982 0.04566 0.0340 0.0085 1.0000
17.750 1.4435 0.05344 0.04938 0.0331 0.0083 1.0000
18.000 1.4367 0.05752 0.05357 0.0318 0.0082 1.0000
18.250 1.4271 0.06215 0.05832 0.0301 0.0081 1.0000
18.500 1.4148 0.06740 0.06369 0.0280 0.0080 1.0000
18.750 1.3988 0.07345 0.06988 0.0252 0.0079 1.0000
19.000 1.3793 0.08023 0.07680 0.0221 0.0078 1.0000
19.250 1.3561 0.08784 0.08456 0.0184 0.0078 1.0000
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Polar data table (+)
Polar graphs
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