TRAINER60 (trainer60-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 50,000 Max Cl/Cd: 24.51 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-trainer60-il-50000-n5.txt Download as CSV file: xf-trainer60-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TRAINER60
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7776 0.10770 0.09913 0.0001 1.0000 0.1582
-13.250 -0.8174 0.09670 0.08810 -0.0051 1.0000 0.1686
-13.000 -0.9330 0.07445 0.06558 -0.0162 1.0000 0.1786
-12.750 -0.8626 0.08235 0.07365 -0.0112 1.0000 0.1858
-12.500 -0.9523 0.06600 0.05700 -0.0188 1.0000 0.1931
-12.250 -0.9479 0.06381 0.05480 -0.0190 1.0000 0.2005
-12.000 -0.9612 0.05951 0.05039 -0.0201 1.0000 0.2078
-11.750 -1.0008 0.05277 0.04336 -0.0215 1.0000 0.2134
-11.500 -0.9667 0.05399 0.04476 -0.0202 1.0000 0.2225
-11.250 -0.9955 0.04915 0.03967 -0.0199 1.0000 0.2287
-11.000 -0.9729 0.04912 0.03977 -0.0190 1.0000 0.2371
-10.750 -0.9822 0.04664 0.03717 -0.0173 1.0000 0.2445
-10.500 -0.9790 0.04518 0.03568 -0.0155 1.0000 0.2519
-10.250 -0.9647 0.04449 0.03500 -0.0142 1.0000 0.2601
-10.000 -0.9715 0.04211 0.03241 -0.0120 1.0000 0.2677
-9.750 -0.9426 0.04220 0.03264 -0.0115 1.0000 0.2751
-9.500 -0.9396 0.04038 0.03064 -0.0098 1.0000 0.2829
-9.250 -0.9213 0.03950 0.02975 -0.0088 1.0000 0.2894
-9.000 -0.9022 0.03873 0.02898 -0.0079 1.0000 0.2963
-8.750 -0.8977 0.03689 0.02689 -0.0062 1.0000 0.3043
-8.500 -0.8712 0.03654 0.02667 -0.0057 1.0000 0.3103
-8.250 -0.8542 0.03561 0.02568 -0.0046 1.0000 0.3177
-8.000 -0.8412 0.03438 0.02434 -0.0033 1.0000 0.3258
-7.750 -0.8179 0.03394 0.02398 -0.0025 1.0000 0.3326
-7.500 -0.8047 0.03284 0.02277 -0.0011 1.0000 0.3417
-7.250 -0.7841 0.03231 0.02230 -0.0001 1.0000 0.3493
-7.000 -0.7674 0.03167 0.02165 0.0013 1.0000 0.3582
-6.750 -0.7534 0.03094 0.02092 0.0030 1.0000 0.3675
-6.500 -0.7371 0.03059 0.02065 0.0047 1.0000 0.3759
-6.250 -0.7302 0.02988 0.01987 0.0071 1.0000 0.3862
-6.000 -0.7089 0.02963 0.01974 0.0077 0.9807 0.3949
-5.750 -0.6615 0.02909 0.01910 0.0034 0.9675 0.4099
-5.500 -0.6123 0.02870 0.01862 -0.0010 0.9552 0.4249
-5.250 -0.5626 0.02861 0.01855 -0.0050 0.9418 0.4378
-5.000 -0.5202 0.02832 0.01815 -0.0081 0.9264 0.4522
-4.750 -0.4812 0.02834 0.01812 -0.0101 0.9102 0.4648
-4.500 -0.4542 0.02835 0.01810 -0.0099 0.8901 0.4760
-4.250 -0.4296 0.02829 0.01796 -0.0093 0.8711 0.4880
-4.000 -0.4044 0.02826 0.01792 -0.0086 0.8537 0.4981
-3.750 -0.3815 0.02814 0.01773 -0.0076 0.8370 0.5099
-3.500 -0.3568 0.02808 0.01765 -0.0066 0.8215 0.5201
-3.250 -0.3329 0.02794 0.01743 -0.0057 0.8079 0.5319
-3.000 -0.3082 0.02785 0.01730 -0.0047 0.7943 0.5422
-2.750 -0.2849 0.02775 0.01715 -0.0036 0.7806 0.5540
-2.500 -0.2595 0.02764 0.01698 -0.0025 0.7694 0.5649
-2.250 -0.2365 0.02760 0.01693 -0.0014 0.7557 0.5768
-2.000 -0.2110 0.02748 0.01675 -0.0004 0.7455 0.5880
-1.750 -0.1874 0.02747 0.01674 0.0006 0.7322 0.5992
-1.500 -0.1623 0.02728 0.01647 0.0015 0.7228 0.6099
-1.250 -0.1377 0.02731 0.01653 0.0023 0.7100 0.6190
-1.000 -0.1140 0.02708 0.01618 0.0032 0.7005 0.6306
-0.750 -0.0878 0.02716 0.01634 0.0037 0.6885 0.6384
-0.500 -0.0623 0.02705 0.01617 0.0044 0.6788 0.6489
-0.250 -0.0364 0.02707 0.01620 0.0048 0.6685 0.6583
0.000 -0.0099 0.02711 0.01626 0.0053 0.6581 0.6678
0.250 0.0158 0.02703 0.01610 0.0058 0.6497 0.6787
0.500 0.0418 0.02721 0.01639 0.0062 0.6383 0.6874
0.750 0.0674 0.02717 0.01628 0.0069 0.6302 0.6990
1.000 0.0926 0.02737 0.01658 0.0074 0.6198 0.7081
1.250 0.1175 0.02744 0.01665 0.0081 0.6102 0.7193
1.500 0.1441 0.02748 0.01669 0.0087 0.6022 0.7296
1.750 0.1672 0.02769 0.01700 0.0095 0.5904 0.7410
2.000 0.1945 0.02758 0.01684 0.0103 0.5815 0.7523
2.250 0.2169 0.02778 0.01714 0.0112 0.5681 0.7642
2.500 0.2447 0.02761 0.01693 0.0120 0.5586 0.7760
2.750 0.2666 0.02782 0.01724 0.0129 0.5452 0.7895
3.000 0.2954 0.02767 0.01707 0.0136 0.5361 0.8015
3.250 0.3175 0.02793 0.01744 0.0144 0.5232 0.8158
3.500 0.3458 0.02780 0.01728 0.0151 0.5142 0.8304
3.750 0.3697 0.02808 0.01769 0.0156 0.5015 0.8457
4.000 0.3985 0.02794 0.01751 0.0161 0.4922 0.8625
4.250 0.4211 0.02820 0.01788 0.0166 0.4794 0.8825
4.500 0.4525 0.02797 0.01759 0.0165 0.4697 0.9025
4.750 0.4826 0.02821 0.01798 0.0154 0.4556 0.9242
5.000 0.5288 0.02820 0.01799 0.0118 0.4425 0.9414
5.250 0.5842 0.02834 0.01820 0.0064 0.4273 0.9530
5.500 0.6384 0.02885 0.01884 0.0008 0.4103 0.9625
6.000 0.7108 0.02969 0.01965 -0.0036 0.3849 1.0000
6.250 0.7227 0.03033 0.02032 -0.0019 0.3739 1.0000
6.500 0.7412 0.03067 0.02057 -0.0006 0.3646 1.0000
6.750 0.7569 0.03145 0.02139 0.0007 0.3541 1.0000
7.000 0.7770 0.03197 0.02186 0.0017 0.3451 1.0000
7.250 0.7952 0.03279 0.02269 0.0026 0.3362 1.0000
7.500 0.8138 0.03360 0.02354 0.0035 0.3273 1.0000
7.750 0.8367 0.03414 0.02399 0.0042 0.3201 1.0000
8.000 0.8510 0.03544 0.02544 0.0052 0.3112 1.0000
8.250 0.8744 0.03599 0.02594 0.0058 0.3045 1.0000
8.500 0.8901 0.03728 0.02733 0.0066 0.2972 1.0000
8.750 0.9063 0.03847 0.02861 0.0074 0.2899 1.0000
9.000 0.9330 0.03886 0.02890 0.0078 0.2841 1.0000
9.250 0.9399 0.04085 0.03112 0.0089 0.2768 1.0000
9.500 0.9563 0.04196 0.03228 0.0097 0.2699 1.0000
9.750 0.9784 0.04255 0.03281 0.0103 0.2628 1.0000
10.000 0.9797 0.04456 0.03500 0.0117 0.2541 1.0000
10.250 1.0043 0.04452 0.03481 0.0124 0.2451 1.0000
10.500 0.9966 0.04706 0.03755 0.0141 0.2367 1.0000
10.750 1.0188 0.04707 0.03737 0.0150 0.2274 1.0000
11.000 1.0006 0.05062 0.04117 0.0161 0.2207 1.0000
11.250 1.0245 0.05057 0.04095 0.0169 0.2119 1.0000
11.500 1.0027 0.05522 0.04586 0.0165 0.2058 1.0000
11.750 0.9999 0.05819 0.04894 0.0161 0.1985 1.0000
12.000 1.0025 0.06070 0.05147 0.0157 0.1914 1.0000
12.250 0.9719 0.06777 0.05879 0.0130 0.1849 1.0000
12.500 0.9947 0.06759 0.05849 0.0138 0.1770 1.0000
12.750 0.9185 0.08244 0.07375 0.0066 0.1707 1.0000
13.000 0.9755 0.07662 0.06770 0.0103 0.1629 1.0000
13.250 0.8479 0.10203 0.09353 -0.0027 0.1536 1.0000
13.500 0.9314 0.09050 0.08182 0.0040 0.1490 1.0000
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Polar data table (+)
Polar graphs
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