SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 100,000 Max Cl/Cd: 36.33 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8020-il-100000-n5.txt Download as CSV file: xf-sd8020-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8020-010-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7123 0.10913 0.10395 -0.0039 1.0000 0.0284
-12.500 -0.8415 0.07300 0.06746 -0.0286 1.0000 0.0245
-12.250 -0.8673 0.06553 0.05973 -0.0340 1.0000 0.0242
-11.750 -0.9034 0.05568 0.04947 -0.0380 1.0000 0.0242
-11.500 -0.9174 0.05196 0.04556 -0.0378 1.0000 0.0245
-11.250 -0.9280 0.04887 0.04228 -0.0365 1.0000 0.0247
-11.000 -0.9350 0.04633 0.03959 -0.0344 1.0000 0.0251
-10.750 -0.9392 0.04411 0.03720 -0.0319 1.0000 0.0257
-10.500 -0.9381 0.04204 0.03495 -0.0297 1.0000 0.0265
-10.250 -0.9338 0.04018 0.03289 -0.0277 1.0000 0.0279
-10.000 -0.9276 0.03819 0.03062 -0.0257 1.0000 0.0295
-9.750 -0.9188 0.03611 0.02818 -0.0237 1.0000 0.0313
-9.500 -0.9073 0.03398 0.02576 -0.0218 1.0000 0.0326
-9.250 -0.8953 0.03208 0.02378 -0.0202 1.0000 0.0342
-9.000 -0.8812 0.03075 0.02236 -0.0186 1.0000 0.0365
-8.750 -0.8656 0.02944 0.02083 -0.0170 1.0000 0.0397
-8.500 -0.8491 0.02801 0.01917 -0.0153 1.0000 0.0426
-8.250 -0.8346 0.02661 0.01776 -0.0136 1.0000 0.0456
-8.000 -0.8182 0.02545 0.01649 -0.0119 1.0000 0.0494
-7.750 -0.8017 0.02431 0.01524 -0.0101 1.0000 0.0550
-7.500 -0.7844 0.02338 0.01426 -0.0085 1.0000 0.0623
-7.250 -0.7677 0.02237 0.01323 -0.0068 1.0000 0.0701
-7.000 -0.7497 0.02151 0.01228 -0.0052 1.0000 0.0802
-6.750 -0.7312 0.02075 0.01149 -0.0037 1.0000 0.0925
-6.500 -0.7127 0.02003 0.01078 -0.0023 1.0000 0.1068
-6.250 -0.6938 0.01935 0.01013 -0.0008 1.0000 0.1228
-6.000 -0.6746 0.01870 0.00950 0.0006 1.0000 0.1399
-5.750 -0.6550 0.01810 0.00888 0.0020 1.0000 0.1589
-5.500 -0.6357 0.01750 0.00835 0.0034 1.0000 0.1789
-5.250 -0.6157 0.01698 0.00785 0.0048 1.0000 0.2017
-5.000 -0.5961 0.01645 0.00741 0.0062 1.0000 0.2268
-4.750 -0.5763 0.01596 0.00700 0.0076 1.0000 0.2547
-4.500 -0.5565 0.01551 0.00664 0.0090 1.0000 0.2852
-4.250 -0.5366 0.01509 0.00629 0.0104 1.0000 0.3176
-4.000 -0.5169 0.01469 0.00602 0.0119 1.0000 0.3524
-3.500 -0.4775 0.01398 0.00557 0.0149 1.0000 0.4274
-3.250 -0.4578 0.01367 0.00538 0.0165 1.0000 0.4667
-3.000 -0.4382 0.01340 0.00526 0.0181 1.0000 0.5073
-2.750 -0.4185 0.01317 0.00517 0.0197 1.0000 0.5484
-2.500 -0.3987 0.01297 0.00513 0.0213 1.0000 0.5895
-2.250 -0.3786 0.01282 0.00512 0.0229 1.0000 0.6302
-2.000 -0.3550 0.01272 0.00514 0.0239 0.9986 0.6719
-1.750 -0.3159 0.01268 0.00522 0.0217 0.9901 0.7179
-1.500 -0.2752 0.01268 0.00533 0.0194 0.9820 0.7601
-1.250 -0.2352 0.01267 0.00538 0.0173 0.9725 0.7985
-1.000 -0.1929 0.01270 0.00547 0.0148 0.9630 0.8321
-0.750 -0.1455 0.01276 0.00556 0.0113 0.9545 0.8609
-0.500 -0.0987 0.01280 0.00562 0.0079 0.9440 0.8852
-0.250 -0.0491 0.01285 0.00567 0.0039 0.9330 0.9039
0.000 0.0000 0.01286 0.00568 0.0000 0.9198 0.9198
0.250 0.0493 0.01285 0.00567 -0.0039 0.9039 0.9330
0.500 0.0988 0.01280 0.00562 -0.0079 0.8852 0.9441
0.750 0.1456 0.01276 0.00556 -0.0113 0.8610 0.9546
1.000 0.1929 0.01270 0.00547 -0.0148 0.8322 0.9630
1.250 0.2352 0.01267 0.00538 -0.0173 0.7985 0.9724
1.500 0.2751 0.01268 0.00532 -0.0194 0.7601 0.9819
1.750 0.3159 0.01268 0.00522 -0.0217 0.7177 0.9901
2.000 0.3552 0.01272 0.00514 -0.0239 0.6723 0.9987
2.250 0.3786 0.01282 0.00512 -0.0229 0.6307 1.0000
2.500 0.3987 0.01297 0.00513 -0.0213 0.5897 1.0000
2.750 0.4185 0.01316 0.00517 -0.0197 0.5485 1.0000
3.000 0.4382 0.01340 0.00526 -0.0181 0.5075 1.0000
3.250 0.4578 0.01367 0.00538 -0.0165 0.4669 1.0000
3.500 0.4775 0.01398 0.00557 -0.0149 0.4273 1.0000
4.000 0.5169 0.01469 0.00602 -0.0119 0.3525 1.0000
4.250 0.5366 0.01509 0.00629 -0.0104 0.3178 1.0000
4.500 0.5565 0.01551 0.00664 -0.0090 0.2854 1.0000
4.750 0.5763 0.01596 0.00700 -0.0076 0.2546 1.0000
5.000 0.5961 0.01645 0.00741 -0.0062 0.2268 1.0000
5.250 0.6157 0.01698 0.00785 -0.0048 0.2016 1.0000
5.500 0.6357 0.01750 0.00835 -0.0034 0.1789 1.0000
5.750 0.6550 0.01810 0.00888 -0.0020 0.1587 1.0000
6.000 0.6746 0.01870 0.00950 -0.0006 0.1396 1.0000
6.250 0.6938 0.01934 0.01013 0.0008 0.1224 1.0000
6.500 0.7126 0.02003 0.01079 0.0023 0.1067 1.0000
6.750 0.7312 0.02076 0.01149 0.0037 0.0924 1.0000
7.000 0.7497 0.02152 0.01228 0.0052 0.0801 1.0000
7.250 0.7676 0.02238 0.01323 0.0068 0.0701 1.0000
7.500 0.7844 0.02339 0.01426 0.0086 0.0625 1.0000
7.750 0.8017 0.02431 0.01525 0.0101 0.0552 1.0000
8.000 0.8182 0.02545 0.01648 0.0118 0.0497 1.0000
8.250 0.8346 0.02661 0.01776 0.0135 0.0457 1.0000
8.500 0.8494 0.02798 0.01915 0.0153 0.0427 1.0000
8.750 0.8656 0.02946 0.02084 0.0170 0.0400 1.0000
9.000 0.8813 0.03075 0.02236 0.0185 0.0366 1.0000
9.250 0.8955 0.03208 0.02379 0.0201 0.0343 1.0000
9.500 0.9076 0.03394 0.02573 0.0218 0.0327 1.0000
9.750 0.9190 0.03610 0.02817 0.0237 0.0314 1.0000
10.000 0.9279 0.03823 0.03065 0.0256 0.0298 1.0000
10.250 0.9341 0.04018 0.03289 0.0277 0.0280 1.0000
10.500 0.9382 0.04209 0.03502 0.0297 0.0266 1.0000
10.750 0.9393 0.04415 0.03725 0.0318 0.0257 1.0000
11.000 0.9352 0.04636 0.03961 0.0344 0.0251 1.0000
11.250 0.9281 0.04893 0.04235 0.0365 0.0247 1.0000
11.500 0.9178 0.05198 0.04557 0.0377 0.0244 1.0000
11.750 0.9036 0.05574 0.04953 0.0379 0.0242 1.0000
12.250 0.8677 0.06557 0.05979 0.0338 0.0242 1.0000
12.500 0.8432 0.07281 0.06726 0.0287 0.0244 1.0000
12.750 0.7123 0.10943 0.10425 0.0037 0.0290 1.0000
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Polar data table (+)
Polar graphs
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