SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 50,000 Max Cl/Cd: 34.94 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6060-il-50000-n5.txt Download as CSV file: xf-sd6060-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6060-104-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4910 0.08675 0.08002 -0.0358 1.0000 0.0363
-9.000 -0.4931 0.08202 0.07534 -0.0385 1.0000 0.0359
-8.750 -0.5003 0.07736 0.07073 -0.0411 1.0000 0.0357
-8.500 -0.5098 0.07333 0.06671 -0.0424 1.0000 0.0354
-8.250 -0.5185 0.06935 0.06270 -0.0432 1.0000 0.0353
-8.000 -0.5254 0.06539 0.05866 -0.0435 1.0000 0.0351
-7.750 -0.5307 0.06154 0.05467 -0.0433 1.0000 0.0350
-7.500 -0.5342 0.05786 0.05080 -0.0426 1.0000 0.0351
-7.250 -0.5361 0.05436 0.04706 -0.0412 1.0000 0.0353
-7.000 -0.5370 0.05106 0.04342 -0.0393 1.0000 0.0358
-6.750 -0.5355 0.04808 0.04005 -0.0369 1.0000 0.0363
-6.500 -0.5325 0.04500 0.03680 -0.0348 1.0000 0.0372
-6.250 -0.5264 0.04249 0.03406 -0.0326 1.0000 0.0381
-6.000 -0.5183 0.04007 0.03131 -0.0303 1.0000 0.0389
-5.750 -0.5080 0.03767 0.02857 -0.0281 1.0000 0.0396
-5.500 -0.4954 0.03541 0.02597 -0.0260 1.0000 0.0406
-5.250 -0.4807 0.03333 0.02356 -0.0240 1.0000 0.0420
-5.000 -0.4640 0.03139 0.02128 -0.0221 1.0000 0.0439
-4.750 -0.4460 0.02982 0.01932 -0.0203 1.0000 0.0477
-4.500 -0.4294 0.02845 0.01790 -0.0188 1.0000 0.0530
-4.250 -0.4107 0.02717 0.01639 -0.0171 1.0000 0.0595
-4.000 -0.3766 0.02579 0.01484 -0.0184 0.9932 0.0746
-3.750 -0.3432 0.02437 0.01346 -0.0199 0.9860 0.1027
-3.500 -0.3107 0.02283 0.01223 -0.0216 0.9789 0.1614
-3.250 -0.2820 0.02108 0.01136 -0.0230 0.9715 0.3071
-3.000 -0.2634 0.01964 0.01133 -0.0210 0.9631 0.5741
-2.750 -0.2332 0.01967 0.01176 -0.0187 0.9572 0.7717
-2.500 -0.1929 0.02007 0.01198 -0.0189 0.9514 0.8705
-2.250 -0.1220 0.02051 0.01195 -0.0255 0.9509 0.9365
-2.000 -0.0332 0.02055 0.01143 -0.0369 0.9528 0.9768
-1.750 0.0361 0.02035 0.01085 -0.0458 0.9502 1.0000
-1.500 0.0731 0.02032 0.01056 -0.0487 0.9406 1.0000
-1.250 0.1082 0.02031 0.01035 -0.0511 0.9305 1.0000
-1.000 0.1379 0.02033 0.01022 -0.0524 0.9189 1.0000
-0.750 0.1670 0.02038 0.01012 -0.0534 0.9078 1.0000
-0.500 0.1968 0.02044 0.01003 -0.0544 0.8975 1.0000
-0.250 0.2267 0.02049 0.00998 -0.0553 0.8873 1.0000
0.000 0.2495 0.02061 0.01001 -0.0549 0.8753 1.0000
0.250 0.2722 0.02074 0.01008 -0.0543 0.8636 1.0000
0.500 0.2956 0.02089 0.01015 -0.0538 0.8525 1.0000
0.750 0.3217 0.02099 0.01020 -0.0537 0.8425 1.0000
1.000 0.3445 0.02114 0.01032 -0.0529 0.8312 1.0000
1.250 0.3650 0.02135 0.01050 -0.0518 0.8192 1.0000
1.500 0.3865 0.02154 0.01068 -0.0507 0.8076 1.0000
1.750 0.4094 0.02170 0.01082 -0.0498 0.7964 1.0000
2.000 0.4348 0.02179 0.01092 -0.0491 0.7860 1.0000
2.250 0.4569 0.02194 0.01111 -0.0479 0.7742 1.0000
2.500 0.4776 0.02214 0.01133 -0.0466 0.7615 1.0000
2.750 0.4991 0.02231 0.01154 -0.0452 0.7488 1.0000
3.000 0.5211 0.02246 0.01174 -0.0439 0.7360 1.0000
3.250 0.5437 0.02260 0.01196 -0.0427 0.7230 1.0000
3.500 0.5666 0.02271 0.01214 -0.0414 0.7095 1.0000
3.750 0.5896 0.02280 0.01231 -0.0401 0.6954 1.0000
4.000 0.6127 0.02288 0.01248 -0.0388 0.6806 1.0000
4.250 0.6360 0.02293 0.01267 -0.0374 0.6651 1.0000
4.500 0.6597 0.02295 0.01279 -0.0360 0.6489 1.0000
4.750 0.6842 0.02292 0.01286 -0.0347 0.6321 1.0000
5.000 0.7047 0.02308 0.01315 -0.0330 0.6118 1.0000
5.250 0.7278 0.02309 0.01332 -0.0315 0.5916 1.0000
5.500 0.7489 0.02322 0.01357 -0.0298 0.5686 1.0000
5.750 0.7708 0.02328 0.01374 -0.0281 0.5442 1.0000
6.000 0.7917 0.02341 0.01397 -0.0264 0.5172 1.0000
6.250 0.8115 0.02364 0.01428 -0.0245 0.4869 1.0000
6.500 0.8307 0.02392 0.01467 -0.0226 0.4540 1.0000
6.750 0.8494 0.02431 0.01503 -0.0207 0.4195 1.0000
7.000 0.8658 0.02490 0.01560 -0.0187 0.3823 1.0000
7.250 0.8808 0.02565 0.01628 -0.0167 0.3450 1.0000
7.500 0.8939 0.02657 0.01709 -0.0145 0.3084 1.0000
7.750 0.9055 0.02765 0.01811 -0.0124 0.2719 1.0000
8.000 0.9149 0.02888 0.01921 -0.0102 0.2378 1.0000
8.250 0.9231 0.03023 0.02051 -0.0081 0.2034 1.0000
8.500 0.9282 0.03177 0.02196 -0.0059 0.1709 1.0000
8.750 0.9307 0.03343 0.02347 -0.0036 0.1393 1.0000
9.000 0.9323 0.03525 0.02512 -0.0013 0.1150 1.0000
9.250 0.9361 0.03722 0.02708 0.0006 0.0941 1.0000
9.500 0.9409 0.03934 0.02919 0.0024 0.0810 1.0000
9.750 0.9484 0.04151 0.03141 0.0041 0.0716 1.0000
10.000 0.9546 0.04366 0.03352 0.0054 0.0647 1.0000
10.250 0.9662 0.04574 0.03587 0.0066 0.0574 1.0000
10.500 0.9754 0.04797 0.03809 0.0077 0.0532 1.0000
10.750 0.9934 0.05047 0.04095 0.0088 0.0501 1.0000
11.000 1.0065 0.05338 0.04427 0.0099 0.0475 1.0000
11.250 1.0128 0.05639 0.04756 0.0108 0.0456 1.0000
11.500 1.0149 0.05942 0.05080 0.0115 0.0440 1.0000
11.750 1.0167 0.06245 0.05388 0.0119 0.0420 1.0000
12.000 1.0086 0.06643 0.05814 0.0121 0.0409 1.0000
12.250 0.9961 0.07089 0.06293 0.0115 0.0403 1.0000
12.500 0.9813 0.07593 0.06826 0.0102 0.0400 1.0000
12.750 0.9643 0.08159 0.07417 0.0080 0.0399 1.0000
13.000 0.9462 0.08784 0.08063 0.0050 0.0400 1.0000
13.250 0.9273 0.09476 0.08771 0.0012 0.0403 1.0000
13.500 0.9069 0.10266 0.09575 -0.0034 0.0406 1.0000
13.750 0.8880 0.11102 0.10420 -0.0084 0.0410 1.0000
14.000 0.8710 0.11976 0.11300 -0.0136 0.0414 1.0000
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Polar data table (+)
Polar graphs
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