SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 200,000 Max Cl/Cd: 46.49 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8020-il-200000-n5.txt Download as CSV file: xf-sd8020-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8226 0.11064 0.10674 -0.0021 1.0000 0.0129
-14.500 -0.8551 0.09855 0.09454 -0.0092 1.0000 0.0128
-14.250 -0.8767 0.08971 0.08560 -0.0145 1.0000 0.0126
-14.000 -0.9012 0.08041 0.07614 -0.0205 1.0000 0.0126
-13.750 -0.9193 0.07292 0.06852 -0.0253 1.0000 0.0124
-13.500 -0.9399 0.06533 0.06072 -0.0305 1.0000 0.0125
-13.250 -0.9555 0.05926 0.05446 -0.0343 1.0000 0.0124
-13.000 -0.9700 0.05389 0.04888 -0.0373 1.0000 0.0125
-12.750 -0.9814 0.04952 0.04430 -0.0390 1.0000 0.0126
-12.500 -0.9920 0.04570 0.04023 -0.0398 1.0000 0.0128
-12.250 -0.9994 0.04263 0.03693 -0.0396 1.0000 0.0129
-12.000 -1.0068 0.03974 0.03388 -0.0385 1.0000 0.0131
-11.750 -1.0120 0.03735 0.03136 -0.0367 1.0000 0.0135
-11.500 -1.0134 0.03552 0.02941 -0.0345 1.0000 0.0138
-11.250 -1.0123 0.03395 0.02772 -0.0319 1.0000 0.0142
-11.000 -1.0096 0.03254 0.02618 -0.0292 1.0000 0.0147
-10.750 -1.0031 0.03111 0.02460 -0.0268 1.0000 0.0152
-10.500 -0.9934 0.02982 0.02315 -0.0248 1.0000 0.0161
-10.250 -0.9816 0.02861 0.02171 -0.0229 1.0000 0.0172
-10.000 -0.9700 0.02727 0.02020 -0.0209 1.0000 0.0180
-9.750 -0.9587 0.02598 0.01886 -0.0189 1.0000 0.0193
-9.500 -0.9444 0.02493 0.01770 -0.0172 1.0000 0.0202
-9.250 -0.9291 0.02392 0.01658 -0.0154 1.0000 0.0215
-9.000 -0.9123 0.02307 0.01559 -0.0138 1.0000 0.0232
-8.750 -0.8969 0.02206 0.01447 -0.0120 1.0000 0.0248
-8.500 -0.8812 0.02110 0.01347 -0.0102 1.0000 0.0267
-8.250 -0.8638 0.02031 0.01257 -0.0086 1.0000 0.0288
-8.000 -0.8456 0.01961 0.01175 -0.0070 1.0000 0.0312
-7.750 -0.8284 0.01879 0.01089 -0.0052 1.0000 0.0347
-7.500 -0.8098 0.01811 0.01017 -0.0037 1.0000 0.0390
-7.250 -0.7909 0.01745 0.00944 -0.0021 1.0000 0.0439
-7.000 -0.7717 0.01684 0.00881 -0.0007 1.0000 0.0508
-6.750 -0.7521 0.01627 0.00823 0.0007 1.0000 0.0592
-6.500 -0.7320 0.01577 0.00772 0.0021 1.0000 0.0691
-6.250 -0.7115 0.01532 0.00725 0.0034 1.0000 0.0797
-6.000 -0.6909 0.01489 0.00682 0.0047 1.0000 0.0911
-5.750 -0.6706 0.01445 0.00642 0.0060 1.0000 0.1051
-5.500 -0.6504 0.01400 0.00603 0.0073 1.0000 0.1229
-5.250 -0.6299 0.01359 0.00569 0.0086 1.0000 0.1419
-5.000 -0.6092 0.01323 0.00537 0.0098 1.0000 0.1603
-4.750 -0.5887 0.01286 0.00507 0.0111 1.0000 0.1807
-4.500 -0.5679 0.01255 0.00481 0.0124 1.0000 0.2019
-4.250 -0.5474 0.01223 0.00455 0.0137 1.0000 0.2249
-4.000 -0.5270 0.01193 0.00435 0.0150 1.0000 0.2505
-3.750 -0.5010 0.01164 0.00416 0.0151 0.9983 0.2810
-3.500 -0.4651 0.01135 0.00400 0.0131 0.9931 0.3184
-3.250 -0.4306 0.01105 0.00382 0.0115 0.9869 0.3576
-3.000 -0.3953 0.01076 0.00369 0.0097 0.9812 0.3988
-2.750 -0.3625 0.01047 0.00355 0.0085 0.9735 0.4396
-2.500 -0.3292 0.01019 0.00343 0.0073 0.9660 0.4813
-2.250 -0.2957 0.00992 0.00331 0.0062 0.9576 0.5233
-2.000 -0.2644 0.00967 0.00320 0.0056 0.9476 0.5636
-1.750 -0.2311 0.00943 0.00312 0.0046 0.9380 0.6029
-1.500 -0.1971 0.00921 0.00303 0.0036 0.9278 0.6410
-1.250 -0.1648 0.00902 0.00296 0.0029 0.9151 0.6773
-1.000 -0.1316 0.00885 0.00290 0.0022 0.9016 0.7115
-0.750 -0.0978 0.00870 0.00285 0.0014 0.8864 0.7436
-0.500 -0.0640 0.00859 0.00281 0.0007 0.8690 0.7731
-0.250 -0.0321 0.00853 0.00278 0.0003 0.8480 0.8002
0.000 0.0000 0.00850 0.00276 0.0000 0.8254 0.8253
0.250 0.0320 0.00853 0.00278 -0.0003 0.8001 0.8479
0.500 0.0641 0.00859 0.00281 -0.0007 0.7732 0.8690
0.750 0.0979 0.00870 0.00285 -0.0014 0.7436 0.8864
1.000 0.1316 0.00885 0.00290 -0.0022 0.7116 0.9016
1.250 0.1648 0.00902 0.00296 -0.0029 0.6771 0.9151
1.500 0.1973 0.00921 0.00303 -0.0036 0.6412 0.9279
1.750 0.2312 0.00943 0.00312 -0.0046 0.6035 0.9381
2.250 0.2956 0.00992 0.00331 -0.0062 0.5238 0.9575
2.500 0.3291 0.01019 0.00342 -0.0073 0.4816 0.9658
2.750 0.3625 0.01047 0.00355 -0.0085 0.4396 0.9735
3.000 0.3954 0.01076 0.00369 -0.0097 0.3984 0.9813
3.250 0.4309 0.01105 0.00382 -0.0115 0.3573 0.9871
3.500 0.4654 0.01135 0.00400 -0.0132 0.3188 0.9932
3.750 0.5013 0.01164 0.00416 -0.0151 0.2811 0.9984
4.000 0.5270 0.01193 0.00435 -0.0150 0.2507 1.0000
4.250 0.5474 0.01223 0.00455 -0.0137 0.2246 1.0000
4.750 0.5887 0.01286 0.00507 -0.0111 0.1805 1.0000
5.250 0.6299 0.01359 0.00569 -0.0086 0.1417 1.0000
5.500 0.6504 0.01399 0.00603 -0.0073 0.1228 1.0000
5.750 0.6706 0.01444 0.00642 -0.0060 0.1054 1.0000
6.000 0.6909 0.01489 0.00682 -0.0047 0.0910 1.0000
6.250 0.7115 0.01532 0.00725 -0.0034 0.0796 1.0000
6.500 0.7320 0.01577 0.00772 -0.0021 0.0691 1.0000
6.750 0.7521 0.01627 0.00823 -0.0007 0.0592 1.0000
7.000 0.7717 0.01684 0.00882 0.0007 0.0509 1.0000
7.250 0.7909 0.01745 0.00944 0.0021 0.0439 1.0000
7.500 0.8098 0.01811 0.01017 0.0037 0.0392 1.0000
7.750 0.8284 0.01878 0.01089 0.0052 0.0349 1.0000
8.000 0.8455 0.01961 0.01175 0.0070 0.0314 1.0000
8.250 0.8639 0.02031 0.01257 0.0086 0.0289 1.0000
8.500 0.8812 0.02110 0.01347 0.0102 0.0269 1.0000
8.750 0.8973 0.02202 0.01444 0.0119 0.0250 1.0000
9.000 0.9122 0.02309 0.01560 0.0138 0.0233 1.0000
9.250 0.9290 0.02394 0.01660 0.0154 0.0217 1.0000
9.500 0.9445 0.02494 0.01772 0.0172 0.0204 1.0000
9.750 0.9592 0.02593 0.01881 0.0189 0.0192 1.0000
10.000 0.9710 0.02717 0.02012 0.0208 0.0182 1.0000
10.250 0.9822 0.02854 0.02164 0.0228 0.0172 1.0000
10.500 0.9939 0.02978 0.02310 0.0247 0.0162 1.0000
10.750 1.0034 0.03112 0.02461 0.0268 0.0153 1.0000
11.000 1.0101 0.03252 0.02616 0.0291 0.0146 1.0000
11.250 1.0132 0.03389 0.02766 0.0318 0.0141 1.0000
11.500 1.0139 0.03549 0.02938 0.0344 0.0138 1.0000
11.750 1.0126 0.03733 0.03133 0.0366 0.0134 1.0000
12.000 1.0073 0.03974 0.03388 0.0384 0.0131 1.0000
12.250 1.0002 0.04260 0.03691 0.0395 0.0129 1.0000
12.500 0.9930 0.04568 0.04021 0.0397 0.0128 1.0000
12.750 0.9837 0.04933 0.04408 0.0390 0.0127 1.0000
13.000 0.9716 0.05379 0.04877 0.0372 0.0126 1.0000
13.250 0.9573 0.05912 0.05432 0.0342 0.0124 1.0000
13.500 0.9400 0.06554 0.06095 0.0301 0.0124 1.0000
13.750 0.9213 0.07281 0.06841 0.0252 0.0124 1.0000
14.000 0.9029 0.08035 0.07608 0.0203 0.0126 1.0000
14.250 0.8801 0.08926 0.08514 0.0146 0.0126 1.0000
14.500 0.8541 0.09920 0.09520 0.0085 0.0128 1.0000
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Polar data table (+)
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