NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 500,000 Max Cl/Cd: 49.56 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0011sc-il-500000.txt Download as CSV file: xf-n0011sc-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7318 0.10342 0.10068 -0.0336 1.0000 0.0283
-13.750 -0.8608 0.06982 0.06675 -0.0560 1.0000 0.0265
-13.500 -0.9135 0.05984 0.05651 -0.0609 1.0000 0.0261
-13.250 -0.9737 0.05178 0.04808 -0.0604 1.0000 0.0258
-13.000 -1.0046 0.04786 0.04393 -0.0571 1.0000 0.0257
-12.750 -1.0286 0.04496 0.04082 -0.0527 1.0000 0.0258
-12.500 -1.0603 0.04164 0.03721 -0.0464 1.0000 0.0256
-12.250 -1.0791 0.03956 0.03491 -0.0405 1.0000 0.0256
-12.000 -1.0950 0.03782 0.03299 -0.0343 1.0000 0.0257
-11.750 -1.1101 0.03635 0.03133 -0.0276 1.0000 0.0257
-11.500 -1.1222 0.03504 0.02985 -0.0211 1.0000 0.0258
-11.250 -1.1263 0.03359 0.02823 -0.0161 1.0000 0.0259
-11.000 -1.1268 0.03219 0.02666 -0.0115 1.0000 0.0261
-10.750 -1.1240 0.03100 0.02531 -0.0074 1.0000 0.0263
-10.500 -1.1197 0.02974 0.02387 -0.0035 1.0000 0.0266
-10.250 -1.1134 0.02855 0.02251 0.0001 1.0000 0.0269
-10.000 -1.1051 0.02742 0.02122 0.0035 1.0000 0.0271
-9.750 -1.0954 0.02644 0.02007 0.0067 1.0000 0.0274
-9.500 -1.0840 0.02551 0.01899 0.0095 1.0000 0.0276
-9.250 -1.0724 0.02489 0.01821 0.0126 1.0000 0.0280
-9.000 -1.0585 0.02336 0.01659 0.0148 1.0000 0.0285
-8.750 -1.0441 0.02253 0.01575 0.0171 1.0000 0.0290
-8.500 -1.0294 0.02197 0.01516 0.0195 1.0000 0.0295
-8.250 -1.0143 0.02139 0.01454 0.0218 1.0000 0.0300
-8.000 -0.9988 0.02076 0.01384 0.0241 1.0000 0.0306
-7.750 -0.9830 0.02020 0.01322 0.0263 1.0000 0.0312
-7.500 -0.9620 0.01964 0.01258 0.0275 0.9995 0.0317
-7.250 -0.9333 0.01919 0.01204 0.0271 0.9978 0.0325
-7.000 -0.9069 0.01828 0.01112 0.0270 0.9960 0.0335
-6.750 -0.8776 0.01786 0.01072 0.0264 0.9944 0.0346
-6.500 -0.8514 0.01747 0.01031 0.0265 0.9923 0.0358
-6.250 -0.8244 0.01712 0.00990 0.0265 0.9900 0.0372
-6.000 -0.7977 0.01656 0.00935 0.0265 0.9878 0.0389
-5.750 -0.7681 0.01626 0.00906 0.0259 0.9861 0.0408
-5.500 -0.7369 0.01605 0.00882 0.0250 0.9848 0.0429
-5.250 -0.7153 0.01553 0.00831 0.0262 0.9813 0.0453
-5.000 -0.6888 0.01525 0.00804 0.0264 0.9786 0.0480
-4.750 -0.6598 0.01494 0.00773 0.0260 0.9764 0.0516
-4.500 -0.6284 0.01472 0.00755 0.0251 0.9748 0.0562
-4.250 -0.5962 0.01446 0.00734 0.0240 0.9736 0.0624
-4.000 -0.5766 0.01416 0.00704 0.0258 0.9689 0.0681
-3.750 -0.5492 0.01389 0.00682 0.0258 0.9660 0.0777
-3.500 -0.5191 0.01358 0.00663 0.0252 0.9639 0.0932
-3.250 -0.4867 0.01332 0.00648 0.0241 0.9623 0.1143
-3.000 -0.4536 0.01301 0.00637 0.0227 0.9611 0.1486
-2.750 -0.4387 0.01264 0.00616 0.0254 0.9548 0.1830
-2.500 -0.4113 0.01222 0.00601 0.0254 0.9519 0.2412
-2.250 -0.3826 0.01168 0.00585 0.0249 0.9497 0.3270
-2.000 -0.3573 0.01089 0.00569 0.0252 0.9478 0.4703
-1.750 -0.3554 0.01019 0.00549 0.0309 0.9394 0.5873
-1.500 -0.3411 0.00936 0.00537 0.0342 0.9356 0.7456
-1.250 -0.2764 0.00928 0.00581 0.0265 0.9379 0.8718
-1.000 -0.2186 0.00953 0.00609 0.0202 0.9389 0.9003
-0.750 -0.1676 0.00970 0.00627 0.0157 0.9377 0.9135
-0.500 -0.1075 0.00959 0.00613 0.0096 0.9351 0.9205
-0.250 -0.0402 0.00958 0.00610 0.0020 0.9338 0.9231
0.000 -0.0134 0.00963 0.00615 0.0029 0.9261 0.9317
0.250 0.0393 0.00956 0.00609 -0.0018 0.9231 0.9337
0.500 0.1063 0.00960 0.00614 -0.0094 0.9207 0.9351
0.750 0.1686 0.00970 0.00627 -0.0160 0.9144 0.9376
1.000 0.2204 0.00952 0.00609 -0.0207 0.9014 0.9386
1.250 0.2762 0.00928 0.00581 -0.0265 0.8719 0.9379
1.500 0.3417 0.00933 0.00538 -0.0344 0.7539 0.9356
1.750 0.3554 0.01019 0.00549 -0.0309 0.5877 0.9394
2.000 0.3566 0.01092 0.00569 -0.0250 0.4633 0.9479
2.250 0.3828 0.01168 0.00585 -0.0250 0.3278 0.9497
2.500 0.4114 0.01221 0.00600 -0.0254 0.2432 0.9519
2.750 0.4387 0.01264 0.00616 -0.0255 0.1831 0.9549
3.000 0.4536 0.01300 0.00636 -0.0228 0.1494 0.9611
3.250 0.4869 0.01332 0.00648 -0.0241 0.1150 0.9623
3.500 0.5189 0.01358 0.00662 -0.0251 0.0922 0.9639
3.750 0.5491 0.01389 0.00682 -0.0257 0.0774 0.9660
4.000 0.5766 0.01416 0.00703 -0.0258 0.0679 0.9689
4.250 0.5963 0.01446 0.00732 -0.0240 0.0618 0.9736
4.500 0.6285 0.01470 0.00752 -0.0251 0.0560 0.9748
4.750 0.6596 0.01497 0.00775 -0.0260 0.0512 0.9765
5.000 0.6888 0.01525 0.00804 -0.0264 0.0480 0.9786
5.250 0.7152 0.01553 0.00831 -0.0262 0.0451 0.9814
5.500 0.7369 0.01604 0.00881 -0.0251 0.0430 0.9848
5.750 0.7683 0.01626 0.00906 -0.0259 0.0408 0.9861
6.000 0.7977 0.01657 0.00935 -0.0265 0.0389 0.9878
6.250 0.8246 0.01712 0.00990 -0.0266 0.0371 0.9900
6.500 0.8518 0.01742 0.01026 -0.0266 0.0356 0.9923
6.750 0.8778 0.01784 0.01069 -0.0264 0.0344 0.9945
7.000 0.9069 0.01830 0.01114 -0.0270 0.0333 0.9961
7.250 0.9336 0.01913 0.01199 -0.0272 0.0323 0.9978
7.500 0.9621 0.01966 0.01260 -0.0275 0.0317 0.9995
7.750 0.9829 0.02018 0.01321 -0.0263 0.0310 1.0000
8.000 0.9987 0.02078 0.01386 -0.0240 0.0304 1.0000
8.250 1.0141 0.02135 0.01449 -0.0218 0.0299 1.0000
8.500 1.0293 0.02199 0.01519 -0.0194 0.0295 1.0000
8.750 1.0440 0.02260 0.01582 -0.0171 0.0289 1.0000
9.000 1.0585 0.02342 0.01667 -0.0148 0.0286 1.0000
9.250 1.0724 0.02491 0.01824 -0.0126 0.0280 1.0000
9.500 1.0843 0.02554 0.01901 -0.0096 0.0277 1.0000
9.750 1.0954 0.02647 0.02010 -0.0067 0.0275 1.0000
10.000 1.1051 0.02748 0.02128 -0.0035 0.0272 1.0000
10.250 1.1133 0.02856 0.02253 -0.0001 0.0269 1.0000
10.500 1.1197 0.02981 0.02395 0.0035 0.0267 1.0000
10.750 1.1237 0.03107 0.02538 0.0075 0.0264 1.0000
11.000 1.1254 0.03245 0.02694 0.0117 0.0262 1.0000
11.250 1.1239 0.03395 0.02864 0.0164 0.0261 1.0000
11.500 1.1210 0.03518 0.03002 0.0213 0.0258 1.0000
11.750 1.1093 0.03644 0.03143 0.0277 0.0257 1.0000
12.000 1.0927 0.03808 0.03327 0.0345 0.0258 1.0000
12.250 1.0739 0.04002 0.03543 0.0411 0.0258 1.0000
12.500 1.0627 0.04147 0.03701 0.0461 0.0255 1.0000
12.750 1.0337 0.04456 0.04038 0.0522 0.0257 1.0000
13.000 1.0142 0.04706 0.04306 0.0564 0.0256 1.0000
13.250 0.9576 0.05345 0.04985 0.0606 0.0260 1.0000
13.500 0.9193 0.05920 0.05584 0.0611 0.0262 1.0000
13.750 0.8565 0.07069 0.06765 0.0552 0.0265 1.0000
14.000 0.7253 0.10506 0.10231 0.0327 0.0282 1.0000
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