RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 89 AIRFOIL (raf89-il) Reynolds number: 100,000 Max Cl/Cd: 18.71 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf89-il-100000.txt Download as CSV file: xf-raf89-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3206 0.13664 0.13041 -0.0522 1.0000 0.1877
-14.250 -0.8773 0.05861 0.05158 -0.0749 1.0000 0.2018
-14.000 -0.9623 0.05497 0.04781 -0.0674 1.0000 0.2019
-13.750 -1.0285 0.05252 0.04522 -0.0604 1.0000 0.2024
-13.500 -1.0870 0.04988 0.04234 -0.0543 0.9991 0.2036
-13.250 -0.9936 0.05271 0.04566 -0.0590 0.9965 0.2122
-13.000 -1.0290 0.04818 0.04072 -0.0594 0.9870 0.2172
-12.750 -0.9685 0.04914 0.04195 -0.0629 0.9828 0.2248
-12.500 -0.9754 0.04671 0.03929 -0.0637 0.9759 0.2312
-12.250 -0.9833 0.04497 0.03740 -0.0620 0.9665 0.2363
-12.000 -0.9316 0.04545 0.03806 -0.0656 0.9622 0.2444
-11.750 -0.9627 0.04350 0.03580 -0.0611 0.9519 0.2490
-11.500 -0.9156 0.04366 0.03616 -0.0641 0.9473 0.2565
-11.250 -0.9080 0.04284 0.03523 -0.0633 0.9416 0.2634
-11.000 -0.9507 0.04209 0.03425 -0.0542 0.9299 0.2662
-10.750 -0.8960 0.04211 0.03447 -0.0586 0.9262 0.2744
-10.500 -0.8882 0.04148 0.03369 -0.0570 0.9208 0.2814
-10.250 -0.9317 0.04110 0.03314 -0.0468 0.9099 0.2838
-10.000 -0.8941 0.04104 0.03323 -0.0487 0.9055 0.2911
-9.750 -0.8724 0.04065 0.03278 -0.0486 0.9009 0.2988
-9.500 -0.9045 0.04021 0.03212 -0.0399 0.8919 0.3025
-9.250 -0.8870 0.04014 0.03216 -0.0387 0.8863 0.3083
-9.000 -0.8623 0.04008 0.03214 -0.0385 0.8816 0.3156
-8.750 -0.8609 0.03917 0.03088 -0.0354 0.8769 0.3231
-8.500 -0.8567 0.03941 0.03131 -0.0317 0.8697 0.3274
-8.250 -0.8492 0.03951 0.03147 -0.0288 0.8636 0.3328
-8.000 -0.8442 0.03899 0.03075 -0.0257 0.8582 0.3400
-7.750 -0.8003 0.03858 0.03041 -0.0287 0.8548 0.3483
-7.500 -0.8040 0.03875 0.03059 -0.0240 0.8484 0.3533
-7.250 -0.8193 0.03863 0.03036 -0.0175 0.8407 0.3581
-7.000 -0.8039 0.03811 0.02972 -0.0159 0.8353 0.3652
-6.750 -0.7550 0.03793 0.02967 -0.0194 0.8318 0.3742
-6.500 -0.7651 0.03789 0.02949 -0.0137 0.8250 0.3798
-6.250 -0.7754 0.03774 0.02923 -0.0081 0.8169 0.3848
-6.000 -0.7363 0.03763 0.02929 -0.0100 0.8118 0.3930
-5.750 -0.7080 0.03710 0.02856 -0.0102 0.8077 0.4028
-5.500 -0.7081 0.03728 0.02882 -0.0061 0.7998 0.4079
-5.250 -0.6984 0.03739 0.02901 -0.0035 0.7922 0.4145
-5.000 -0.6772 0.03695 0.02838 -0.0025 0.7867 0.4241
-4.750 -0.6191 0.03670 0.02835 -0.0071 0.7834 0.4343
-4.500 -0.6450 0.03722 0.02883 0.0008 0.7727 0.4389
-4.250 -0.6282 0.03702 0.02858 0.0024 0.7657 0.4476
-4.000 -0.5815 0.03689 0.02857 -0.0002 0.7614 0.4582
-3.750 -0.5673 0.03694 0.02856 0.0019 0.7549 0.4675
-3.500 -0.5704 0.03745 0.02918 0.0063 0.7443 0.4732
-3.000 -0.4824 0.03713 0.02894 0.0023 0.7360 0.4967
-2.750 -0.5165 0.03799 0.02974 0.0110 0.7220 0.5025
-2.500 -0.4787 0.03798 0.02982 0.0100 0.7165 0.5131
-2.250 -0.4365 0.03766 0.02942 0.0085 0.7132 0.5275
-2.000 -0.4579 0.03877 0.03063 0.0151 0.6994 0.5325
-1.750 -0.4291 0.03863 0.03040 0.0156 0.6938 0.5467
-1.500 -0.3764 0.03843 0.03034 0.0128 0.6907 0.5590
-1.250 -0.4076 0.03946 0.03128 0.0206 0.6763 0.5684
-1.000 -0.3674 0.03939 0.03134 0.0195 0.6715 0.5803
-0.750 -0.3247 0.03890 0.03082 0.0184 0.6685 0.5961
-0.500 -0.3476 0.04020 0.03219 0.0248 0.6539 0.6041
-0.250 -0.3139 0.03986 0.03184 0.0247 0.6494 0.6196
0.000 -0.2713 0.03939 0.03138 0.0238 0.6467 0.6361
0.250 -0.2965 0.04085 0.03291 0.0301 0.6318 0.6443
0.500 -0.2613 0.04046 0.03251 0.0302 0.6278 0.6607
0.750 -0.2103 0.03995 0.03211 0.0282 0.6255 0.6743
1.000 -0.2486 0.04165 0.03375 0.0360 0.6102 0.6855
1.250 -0.2034 0.04133 0.03355 0.0347 0.6068 0.6980
1.500 -0.1594 0.04056 0.03276 0.0339 0.6047 0.7130
1.750 -0.1915 0.04268 0.03495 0.0404 0.5893 0.7215
2.000 -0.1570 0.04216 0.03440 0.0406 0.5861 0.7356
2.250 -0.1071 0.04140 0.03369 0.0391 0.5843 0.7483
2.500 -0.1503 0.04372 0.03599 0.0466 0.5686 0.7582
2.750 -0.1050 0.04311 0.03544 0.0454 0.5659 0.7695
3.000 -0.0815 0.04293 0.03521 0.0467 0.5618 0.7819
3.250 -0.1007 0.04496 0.03733 0.0509 0.5484 0.7908
3.500 -0.0661 0.04413 0.03645 0.0515 0.5458 0.8040
3.750 -0.0250 0.04384 0.03622 0.0502 0.5423 0.8142
4.000 -0.0594 0.04640 0.03882 0.0557 0.5283 0.8255
4.250 -0.0078 0.04553 0.03798 0.0536 0.5261 0.8365
4.500 -0.0396 0.04867 0.04118 0.0576 0.5121 0.8483
4.750 0.0101 0.04829 0.04084 0.0549 0.5086 0.8598
5.000 0.0606 0.04730 0.03985 0.0530 0.5066 0.8730
5.250 0.0516 0.05126 0.04394 0.0521 0.4922 0.8837
5.500 0.1020 0.05082 0.04351 0.0493 0.4890 0.8973
5.750 0.1794 0.04979 0.04252 0.0433 0.4873 0.9055
6.000 0.2297 0.04969 0.04244 0.0400 0.4837 0.9177
6.250 0.3259 0.04713 0.03986 0.0331 0.4844 0.9245
6.500 0.4160 0.04472 0.03744 0.0268 0.4844 0.9312
6.750 0.4980 0.04200 0.03466 0.0219 0.4845 0.9390
7.000 0.6061 0.03859 0.03114 0.0138 0.4844 0.9402
7.250 0.5300 0.04731 0.04010 0.0170 0.4642 0.9572
7.500 0.6236 0.04412 0.03686 0.0107 0.4638 0.9609
7.750 0.7393 0.03991 0.03252 0.0024 0.4636 0.9625
8.000 0.5137 0.06459 0.05767 0.0068 0.4242 0.9903
8.250 0.6060 0.06064 0.05369 0.0011 0.4249 0.9982
8.500 0.6223 0.05645 0.04935 0.0051 0.4259 1.0000
8.750 0.6629 0.05261 0.04536 0.0071 0.4263 1.0000
9.000 0.7267 0.04875 0.04138 0.0064 0.4264 1.0000
9.250 0.8234 0.04400 0.03650 0.0022 0.4263 1.0000
11.000 0.4102 0.09955 0.09220 0.0201 0.3494 1.0000
11.250 0.3632 0.10774 0.10046 0.0191 0.3447 1.0000
11.500 0.3587 0.11128 0.10401 0.0189 0.3411 1.0000
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